Abstract: In one embodiment, a control device for a trim tab of a boat includes a plurality of stabilizers, one of each provided on each side of the boat, and a joystick. The stabilizers include blades and a control actuator for each blade, which determines the regulation of the angle of each blade in respect of a plane identifying the transom of the boat. The joystick is connected to a control circuit, which generates a command signal based on a movement of the joystick and coordinates the position of each of the stabilizers, thereby causing the bow of the boat to move in the same direction as the joystick.

Abstract: An attitude-adaptive hydrofoil apparatus, including: strut-braced wing assemblies, a horizontal wing assembly, connection plates, and attack angle adjusting plates. The strut-braced wing assemblies each include a bearing, at least one inclined tube, at least one inclined flow-guiding wing, and at least one stop dog. The horizontal wing assembly includes a horizontal tube, at least one horizontal flow-guiding wing, and at least one depth-locating wing. The attack angle adjusting plates each include an angle adjusting end plate having a hole. The strut-braced wing assemblies are symmetrically disposed at two sides of the horizontal wing assembly. The bearing is fixed on a vessel body by welding. The at least one inclined flow-guiding wing is sleeved on the at least one inclined tube, and is limited by the at least one stop dog. The attack angle adjusting plates are disposed at two ends of the horizontal tube, respectively.

Abstract: A marine hull including a hull plate manufactured from metal, a set of longitudinal reinforcements and a set of transverse reinforcements, at least one longitudinal reinforcement of the set of longitudinal reinforcements being arranged between the hull plate and at least one transverse reinforcement of the set of transverse reinforcements, and being connected to an inside of the hull plate. The marine hull is characterized in that the hull plate has a thickness that is less than 10 mm, and that the at least one longitudinal reinforcement is manufactured from the same metal as the hull plate and comprises at least one resilient segment arranged to spring in the direction transverse to the thickness of the hull plate, and that the resilient segment is arranged to bottom upon a compression that is more than 10 mm and less than 50 mm.

Abstract: An anchor device and method for safely and reliably securing watercraft to the bed of a body of water is provided. The anchor device may include a handle member with detachable components and an auger. The auger may be bored into the ground upon rotation of the handle member and then detached from the handle member by lifting the handle member vertically. The auger may include a shaft with a square cross-section and a pointed bottom end. Two auger blades, separated by an axial gap, may be attached to the shaft. Each auger blade may extend circumferentially around the shaft in a helical configuration.

Abstract: System for mooring a large vessel for production of hydrocarbons, such vessel for example being a FPSO vessel, the mooring system comprising at least two floating bodies of the hang-off type, moored by means of differentiated compliance spread anchoring system to the sea bed, allowing partly weathervaning of the large vessel; a riser system extending from the sea bed to each the floating bodies, and means for transfer of fluids from the two floating bodies to the large vessel, the floating bodies and the large vessel being provided with locking means, locking floating bodies to the large vessel at the bow and the stern of the vessel in a mechanically rigid manner, thus providing a integrated, rigidly fixed unit comprising the large vessel and the floating bodies.

Abstract: The present disclosure relates generally to knee braces for boats. The knee braces described herein are particularly suitable for use with lightweight, inflatable rafts and kayaks, for example packrafts used in backcountry boating. The knee braces include a fabric body and a plurality of adjustable straps configured to attach the fabric body to a side wall of the boat.

Abstract: Disclosed herein is a paddle board and a manufacturing method thereof, and in particular a paddle board and a manufacturing method thereof wherein a board body is formed of a double space sheet to accommodate air therein, thus obtaining a light structure and an easier storage and transfer, and a wedge part is formed at a lower side of a front end of a board so as to guide the current of water, thus enhancing speed feeling when in use.

Abstract: There is provided a navigation route generation device with which a host moving body can be navigated by offsetting it parallel to a line on the current travel direction of the host moving body by a simple operation, without changing the preset destination or bearing. A plotter that is part of an automatic steering system of a ship comprises a current route acquisition component, a parallel route generator, and a navigation route setting component. The current route acquisition component acquires the travel direction of the host ship. The parallel route generator generates a parallel route, which is a route that is parallel to the travel direction acquired by the current route acquisition component. The navigation route setting component sets the parallel route generated by the parallel route generator to the navigation route of the host ship.

Abstract: An open ended enclosure with a top, sides, and a bottom, where the sides and the bottom form an interior enclosed space. A buoyant device and an inflatable device are provided, where the buoyant device and the inflatable device are connected to form a combination and where the combination is connected with the top of the open ended enclosure. The sides connect the top and the bottom and the sides form a flexible wall and where the flexible wall consists of a combination of at least three layers, a first, outer, layer, a second, middle, layer and a third, inner, layer. The third layer is connected to the second layer and the second layer is connected to the first layer, and, further, the first layer is a water impervious layer, the second layer is a bioelectrical blocking layer and the third layer is a sound emission blocking layer.

Abstract: This disclosure is generally drawn to systems, devices, apparatuses, and/or methods, related to personal flotation devices (PFDs). Specifically, the disclosed systems, devices, apparatuses, and/or methods relate to PFDs having one or more integrated tethers that may allow a PFD (and its wearer) to be coupled to another PFD (and its wearer) via the integrated tether(s). In some examples, a personal flotation device may include a vest including a buoyant component adapted to float in a body of water, and at least one tether. Each tether may include a first end fixed to the vest and a second end detachably coupled to the vest.

Abstract: A dry snorkel for diving comprises a snorkel tube, a float valve and a dry-type top discharge head. A soft plastic waterproof ring is mounted on a top end of the snorkel tube. The soft plastic waterproof ring has an air inlet communicating with the snorkel tube. A curved part is formed on the top end of the snorkel tube. The float valve is pivotally connected to a lower portion of the curved part. When a snorkel is under water, the float valve is turned up by the buoyancy of water to close the air inlet. When the top of the snorkel is above water, the float valve is turned down to open the air inlet. This design is simple and easy to assemble. It has few components and decreases the occurrence of choking on water efficiently whereby the diver breathes easily and comfortably and prolongs the diving time.

Abstract: Dive computers in accordance with embodiments of the invention are disclosed. One embodiment includes a mobile phone handset, including a microprocessor, a microphone connected to the microprocessor, a speaker connected to the microprocessor, a telephone transceiver connected to the microprocessor, memory, a display, and an external connector for communicating with external devices wherein the memory contains a software application, and a waterproof housing including a pressure transducer, where the mobile phone handset is located within the waterproof housing and connected to the pressure transducer via the external connector, and wherein the software application configures the mobile phone handset to create a dive log stored in memory, wherein the dive log comprises recorded information including depth of submersion information recorded from the pressure transducer and display the recorded information during the dive.

Abstract: A vibration-powered device adapted for flotation and propulsion on an upper surface in a liquid. The device having a body with a top side adapted to be at least partially disposed above the surface of the liquid, and a bottom side adapted to be at least partially submerged below the surface of the liquid. A vibration mechanism is disposed in the body. A propulsion fin is connected to the body. The fin includes a top side adapted to be disposed at least partially above the liquid surface, a bottom side adapted to be disposed at least partially below the surface. The vibration mechanism is adapted to oscillate the free distal end of the propulsion fin upward and downward.

Abstract: A method is described for steering of an un-manned ocean vessel (10), where the vessel comprises a hull (12), a self-tacking wing sail (16) for propulsion, a keel (18) for direction stability and a rudder (20).

Abstract: A one-handed paddle for use in pairs with paddleboards, each paddle comprising a longitudinal main shaft, an axial ski pole type grip on the upper end of the shaft and aligned with the shaft axis, an elongated elastic wrist/arm strap on an upper surface of the shaft near the grip defining a tunnel for the arm generally parallel to the shaft in an unstretched condition, and a blade on the lower end of the shaft, the blade set at an acute upward angle to the main axis of the shaft. The blade has an inverted, rounded L-shape, with an inwardly-facing upper shoulder extending inwardly above and beyond a lower inner edge of the blade, the shoulder configured to ride along the upper surface of a paddleboard during the push portion of a paddling stroke.

Abstract: A transom mount has a transom mounting bracket and a leveling platform angularly adjustable relative to the transom mounting bracket. The leveling platform includes a vertical axis pintle, and a spring pin. Supported through the pintle onto the leveling platform is a carousel including rotary limit holes and a travel lock hole. The carousel generally spins freely about the pintle. However, when the spring pin is aligned with these carousel holes, it will automatically lock the carousel relative to the leveling platform. Supported on the carousel is a bell housing or other equivalent support having an engine coupling flange on one end and a long shaft coupler on the other. A set of tilt stop holes may be provided in combination with a tilt stop pin to control the maximum tilt of the bell housing and mud motor drive.

Abstract: Marine engine includes a cylinder block having first and second banks of cylinders that are disposed along a longitudinal axis and extend transversely with respect to each other in a V-shape so as to define a valley therebetween. A catalyst receptacle is disposed at least partially in the valley and contains at least one catalyst that treats exhaust gas from the marine engine. A conduit conveys the exhaust gas from the marine engine to the catalyst receptacle. The conduit receives the exhaust gas from the first and second banks of cylinders and conveys the exhaust gas to the catalyst receptacle. The conduit reverses direction only once with respect to the longitudinal axis.

Abstract: An energy-absorbing (EA) beam member and having a cell core structure is positioned in an aircraft fuselage proximate to the floor of the aircraft. The cell core structure has a length oriented along a width of the fuselage, a width oriented along a length of the fuselage, and a depth extending away from the floor. The cell core structure also includes cell walls that collectively define a repeating conusoidal pattern of alternating respective larger and smaller first and second radii along the length of the cell core structure. The cell walls slope away from a direction of flight of the aircraft at a calibrated lean angle. An EA beam member may include the cell core structure and first and second plates along the length of the cell core structure on opposite edges of the cell material.

Abstract: A bearing block to support and guide movement of a slat support arm forming part of a slat support assembly in which the slat support arm is movable to deploy a slat attached to one end of said slat support arm from a leading edge of an aircraft wing is disclosed. The bearing block comprises a plurality of bearings mountable therein so as to lie in rolling contact with an associated bearing track on a slat support arm extending through the bearing block. Each bearing comprises a bearing element rotatable about a shaft fixed to the bearing block an and is configured so that an axis of rotation of each bearing element angularly adjusts, relative to an axis of the shaft on which it is rotatably mounted, to compensate for misalignment between said shaft and an associated bearing track. A slat support assembly and an aircraft wing is also disclosed.

Abstract: A rotary device assembly is provided and includes an input shaft coupled to a torque generating device, an output shaft and a rotary device disposed to transmit first torque from the input shaft to the output shaft and configured with no-back capability to prevent second torque applied to the output shaft from being transmitted to the input shaft in an event the second torque deceeds a torque-limiting threshold and the no-back capability and torsional lock-up capability to prevent an overload of the torque generating device in an event the second torque exceeds the torque-limiting threshold.

Abstract: Generally, a mechanically self-regulating propeller is described which may have a central hub unit disposed around a shaft member, at least two blades coupled to the central hub unit, at least one timing hub coupled to each of the at least two blades, and a hydraulic unit coupled to the at least one timing hub. The at least one timing hub is slidably engaged to the shaft member. When not in use the blades lay substantially parallel to the central hub unit. When the central hub unit is rotated the blades begin to open or fan out to a position that is substantially perpendicular to the central hub unit. The propeller may be used any number of implementations including vehicles, generators, and any other mechanism requiring a propeller or similarly structured device.

Abstract: The device is intended to supply a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller, according to separate operating states, from a rotary power assembly, the device being arranged so as to be located between the power assembly and the actuator, along a longitudinal axis, and being connected in rotation therewith. According to the invention, the device comprises supplies for supplying fluid interacting with the power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor to which the supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by a tubular equipment connected to the distributor.

Abstract: A system includes an auto-flight system and a touchscreen flight mode control panel. The auto-flight system is configured to control a plurality of primary flight modes. The touchscreen flight mode control panel is communicatively coupled to the auto-flight system. The touchscreen flight mode control panel is configured to receive primary flight mode data from the auto-flight system. The touchscreen flight mode control panel is also configured to graphically present each primary flight mode of the plurality of primary flight modes to a user. The touchscreen flight mode control panel is further configured to detect touch gestures and direct executions of the user. The touchscreen flight mode control panel is additionally configured to output touch gesture data and direct execution data to the auto-flight system.

Abstract: An asymmetric multirotor helicopter has a structure supporting at least one main and two secondary propulsion systems. A flight control unit controls the helicopter by varying the relative speed of each of the main and secondary propulsion systems. Each main propulsion system includes at least one main motor drive and a main drive shaft that carries and propels a main differential contra-rotating transmission configured to share the power provided by the main drive shaft with two contra-rotating output shafts. Each secondary propulsion system includes at least one secondary motor drive and a secondary drive shaft that carries and propels respective secondary propulsion blades. The two contra-rotating output shafts support and propel for mutually contra-rotation motion two sets of main propulsion blades. The main drive shaft rotates in the same direction as one of the secondary drive shafts and at least one secondary drive shaft rotates in an opposite direction.

Abstract: An aircraft (10) comprising a fuselage (12) having a longitudinal axis (16), at least one helicopter main rotor (40) operably mounted to the fuselage (12), the at least one helicopter main rotor (40) comprising rotor blades (41) rotatable about a rotation axis (44), wherein the rotor blades (41) can be stopped in flight and adapted to provide symmetrical wing surfaces relative to the longitudinal axis (16); and the aircraft (10) having at least one control surface (62, 82) operable to provide a relative airflow (306) in flight substantially aligned with the rotation axis (44) of the at least one helicopter main rotor (40).

Abstract: An aircraft rotor head is provided and includes a rotor hub including a central portion and radial arms extending outwardly from the central portion, blade retention yokes, each blade retention yoke being pivotably coupled to a corresponding one of the radial arms at one end and to a corresponding blade at another end and a lag restraint star rotatable about and translatable along the central portion. The lag restraint star is coupled to each of the blade retention yokes to facilitate uniform blade lead/lag and uniform blade coning.

Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

Abstract: An unmanned aerial vehicle/unmanned aircraft system including an airframe; a plurality of rotor assemblies respectively extending from a plurality of arms connected to said airframe, said rotor assemblies each having a rotor thereon with at least one rotor blade; a landing gear extending from said airframe; and a flight controller disposed on said airframe; wherein said flight controller receives instructions for unmanned aerial vehicle/unmanned aircraft system control.

Abstract: A rotating wing includes a support frame, two connecting rods, two drive systems and a wing frame. The support frame includes a first side frame, a second side frame, a cross frame member, a first guide pin and a second guide pin. The cross frame member is secured to one end of the first and second side frames. A first connecting rod is rotatably retained on the first side frame. A second connecting rod is rotatably retained on the second side frame. The first guide pin extends from the first side frame and the second guide pin extends from the second side frame. The wing frame includes first and second side members. A peripheral groove is formed in an outer surface of the first and second side members to receive the first and second guide pins. First and second drive systems rotate the first and second connecting rods.

Abstract: A gatebox for an aircraft comprises an opening operable to allow material to flow out of the gatebox, a hopper operable to direct material in the gatebox to the opening, a door coupled to the hopper and operable to move between an open position and a closed position by sliding along a surface of the gatebox, wherein the door comprises a front edge, a rear edge wider than the front edge, and at least two side edges that taper between the front edge and the rear edge, and a seal coupled to the hopper and operable to, when the door is in the closed position, engage the edges of the door and compress to prevent material in the gatebox from being released through the opening along the engaged edge of the door.

Abstract: A holding device for a display and/or operating unit for use in an aircraft on an aircraft seat is proposed, with a holding arm and an attachment device and a coupling unit for connecting the display and/or operating unit, wherein one end region of the holding arm is provided on the attachment device so as to be pivotable about an axis of rotation and the coupling unit for pivotably connecting the display and/or operating unit is provided on the opposite end region of the holding arm, and wherein the holding arm can take up a use position and a storage position on the attachment device. According to the invention, a spiral spring unit is arranged between the attachment device and the holding arm is such a manner that a torque is exerted on the holding arm by the spiral spring unit.

Abstract: The present invention relates to a seat for a vehicle, particularly an aircraft, having a visual playback device integrated in a surface of the seat. A base firmly connected to the seat is arranged in the surface of the seat. Said visual playback device is releasably attached to the base by means of a holder adapted to the visual playback device and the base.

Abstract: A wearable device for operating one or more aircraft related systems, a device system comprising a plurality of such wearable devices, a system comprising such a wearable device and one or more aircraft related systems, and an aircraft comprising such a device system. The wearable device comprises: a user interface configured to receive a user input and to output information corresponding to the received user input; a system interface to connect the wearable device to the aircraft related systems; and a control unit configured to communicate with the aircraft related systems via the system interface to operate at least one of the aircraft related systems and to receive information from at least one of the aircraft related systems. The user interface is further configured to output the information received from the at least one of the aircraft related systems.

Abstract: A water supply module 10? for a transportation means comprises a receiving connection 16? for receiving water from a supply line, a delivery connection 20? for delivering water to a faucet 30?, a control connection 22? for receiving control commands of an actuating element 76 on the faucet 30?, and a control unit 80. The control unit 80 is designed, on the basis of control commands of the actuating element 76, to adjust the delivery of water from the delivery connection 20? to the faucet 30?. The water supply module 10? is designed as an assembly.

Abstract: A system and method of altering the air conditioning system in an aircraft so that the air conditioning system is electrically powered rather than engine powered. The aircraft is rid of the air conditioning components that are dedicated to the engine powered system. A new electric compressor, evaporator and condenser blower assembly are then installed. Heat exchanger units are installed in the areas of the aircraft that are to be cooled. The new air conditioning system has two circulatory loops. In a refrigerant loop, refrigerant is circulated between the electric compressor, evaporator and condenser. This cools the evaporator. The evaporator is then used to cool circulating liquid coolant. The coolant is circulated to the heat exchange units.

Abstract: The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin.

Abstract: A system for controlling a cooling system comprises an operating state detection unit adapted to detect operating signals characteristic of the operating state of the cooling system and/or the operating state of a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system and a database in which priority data dependent on the operating state and characteristic of the priority to be given to the cooling energy consumers in terms of the cooling energy to be supplied in various operating states of the cooling system and/or of the cooling energy consumers, is stored for a plurality of cooling energy consumers to be supplied with cooling energy by the cooling system.

Abstract: The present invention aims to provide a structure which can reduce the scale of modification of an airframe and allows a device to be installed outside the aircraft to be easily mounted onto the airframe. An aircraft includes, as a structure for mounting a measuring device to be installed outside the aircraft onto the airframe: an arm which penetrates the airframe inwardly and outwardly through a window, and has a portion to be provided with the measuring device and a portion located inside the aircraft; seat rails which support seats disposed inside the aircraft; and a mount which is connected with the arm inside the aircraft and transmits a load input from the arm to the seat rails.

Abstract: A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.

Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes receiving, from one or more sensors installed on the aircraft, one or more measurements representative of at least one load applied against the aircraft component; selecting at least one usage model from a plurality of usage models, each usage model of the plurality of usage models relating aircraft loads with received sensor data; determining at least one load value based on the selected at least one usage model and the received one or more measurements; and calculating, based on the determined at least one load value, an amount of change in probability of failure caused by application of the at least one load against the aircraft component.

Abstract: According to an aspect of the invention, a method of probabilistic safe landing area determination for an aircraft includes receiving sensor data indicative of current conditions at potential landing areas for the aircraft. Feature extraction on the sensor data is performed. A processing subsystem of the aircraft updates a probabilistic safe landing area map based on comparing extracted features of the sensor data with a probabilistic safe landing area model. The probabilistic safe landing area model defines probabilities that terrain features are suitable for safe landing of the aircraft. A list of ranked landing areas is generated based on the probabilistic safe landing area map.

Abstract: A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met.

Abstract: A fuselage structure for a rotorcraft (1), the structure comprising load-bearing members including middle frames (9a, 9b) carrying a top floor (12a) and a middle floor (12b). The middle floor (12b) internally partitions the fuselage into two compartments (6, 7), including a cabin-forming top compartment (6) and a bottom compartment (7) having an open bottom (23) leading to the outside via the bottom face of the fuselage. The middle floor (12b) provides a loading plane in the top compartment (6) having a false-floor (27) made up of interchangeable slabs (28) fitted out in a variety of ways. The middle floor (12b) also forms an anchor member from which equipment (16, 17) for suspending can be suspended, which equipment is accessible from outside the fuselage through said open bottom (23).

Abstract: A vehicle cabin arrangement for a vehicle body and a method for lighting a vehicle cabin and for displaying information using such a vehicle cabin arrangement are disclosed. A lighting device with a light-emitting surface directed towards the cabin interior space is provided on a ceiling section. The lighting device has separate lighting elements each having a dedicated light-emitting element surface, which lighting elements can assume different switch-on states and/or light emission states which differ in at least one property of the emitted light. A control device for controlling the lighting device is provided. The lighting elements are arranged so that, both in the direction parallel to the cabin longitudinal axis and in the direction perpendicular to the cabin longitudinal axis, element surfaces are arranged next to one another. The control device can control each lighting element individually with respect to its switch-on state and/or its light emission state.

Abstract: A method for controlling an attitude control system (30) for a space vehicle (10), the attitude of the space vehicle being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed. In an attitude control system that includes a maneuvering subsystem (300) which includes at least one reaction wheel, the method includes, during the at least one preparation phase, a preparation step (50), during which commands are issued to the maneuvering subsystem in order to control the attitude of the space vehicle, followed by a step (55) of stopping the at least one reaction wheel prior to the observation phase. In addition, during the observation phase, a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem, is sent commands in order to control the space vehicle's attitude. An attitude control system for a space vehicle is also described.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Abstract: An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

Abstract: The process validates measurement data that are consistent with the current orbit or allowable maneuvers for Earth-orbiting satellites. The validated data may be processed to detect both large and small maneuvers; large maneuvers that may have been rejected by standard data validation process and small maneuvers that may have been missed. Large maneuvers may present as “trends” in the residuals above the noise threshold from multiple sensors. Small maneuvers may present as a deviation from the expected orbit. The OD engine is suitably configured (as per normal operation) to enforce data reduction on any outliers (e.g. >3 sigma). The maneuver estimation routines employ an objective function for selection of maneuver estimates that combines a residual fit to the current orbit and maneuver, orbit consistency and a penalty for validated but unused data (data that is rejected by the OD engine).

Abstract: An automated method for forming a packaged good article includes establishing a continuous path of travel for a mandrel. The mandrel defines an open interior between a package side and a loading side. With the mandrel at a first angle, a packaging material is wrapped about the mandrel at a first station along the path of travel to define a partial package. Product is dispensed into the partial package at a second station. With the mandrel at the second angle, the partial package and the mandrel are separated from one another at a third station. The first angle of the mandrel (at the first station) differs from the second angle of the mandrel (at the third station). The partial package is closed to form a packaged good article. In some embodiments, the mandrel is horizontal at the first station and is vertical at the third station.

Abstract: A filling aid. The filling aid includes a locking portion including a groove feature; and a locking feature having a locked and an unlocked position; and a filling syringe holder slidably attached to the locking portion, the filling syringe holder including a filling needle cradle portion having a tongue feature; and a needle housing portion comprising at least one tab having a starting position and a filling position, wherein the groove feature configured to accommodate the tongue feature, and wherein the locking feature interact with the filling syringe holder wherein when the locking feature moves from the locked position to the unlocked position the needle housing portion moves from the starting position to the filling position.