Abstract: An inflatable life raft assembly is disclosed, including a deployable and inflatable life raft that a user can voluntarily and repeatedly deploy from a storage carrier, inflate for use, and fold back into the container after use. The carrier is integrally formed with or permanently attached to the inflatable life raft. A compressed gas cylinder can assist the user in inflating the life raft. The storage carrier can automatically open when the life raft inflates, by pressure exerted from within the carrier by the expanding life raft. The inflatable life raft includes weight inserts to render the life raft assembly throwable, both when the life raft is folded and stored in the carrier, and when the life raft is deployed and inflated, greatly assisting a user in tossing or throwing the life raft to a person in need of a floating aid.

Abstract: A man-overboard rescue and retrieval system includes a net assembly having a pair of laterally spaced apart side ropes and a plurality of net portions, each net portion being constructed of a material that floats, extends laterally between the side ropes, and is spaced apart longitudinally from an adjacent net portion. The system includes a deployment capsule defining an interior space configured to selectively receive the net assembly therein. A launching device includes a framework configured to receive the deployment member. A first compressed air canister is in fluid communication with the launching device and the deployment member and configured to apply force to the deployment member when actuated that is sufficient to propel the deployment member from the launching device. Each net portion includes a net spreader connected to a second compressed air canister for selective inflation thereof so as to spread apart the side ropes and net portions.

Abstract: The present invention is generally directed to a floatation device for a snorkel, including a body made from a buoyant material; and an orifice penetrating through the body, the orifice sized to receive a snorkel, such that the floatation device provides sufficient buoyancy to float a snorkel and an attached mask on the surface of water. More specifically, the body may be brightly colored and the orifice may be sized to cause an interference fit with an inserted snorkel. In accordance with some embodiments, the body may be wrapped or covered in a second material.

Abstract: A method for cycling autonomous underwater vehicles (AUVs) that record seismic signals during a marine seismic survey. The method includes deploying plural current AUVs on the ocean bottom; recording the seismic signals during the marine seismic survey with plural current AUVs; releasing from an underwater base a new AUV to replace a corresponding current AUV from the plural current AUVs; recovering the current AUV; and continuing to record the seismic signals with the new AUV.

Abstract: A process of printing an image or images on the sails of a watercraft or other wind powered vessel without altering or compromising the efficacy of the sails is described. The process employs a method of printing large-scale, single or multiple panel, continuous, high-resolution photographic and graphic images on sails. The dynamics and curvatures of a sail are integrated into manufacturing process when employed for sails, though the process may be applied to any large-scaled fabric print. The process of the present invention produces printed sails providing for the highest resolution photographic, art, and graphic printing with virtually no weight gain, nor effect on the sail's original performance. Modern equipment is employed to achieve printing of realistic, high quality images directly on to the fabric of sails without compromising flexibility or durability, as well as without infringing on the speed and agility of the sailing craft.

Abstract: A ballast water treatment apparatus for a ship includes a water collection part for collecting sea water, a forward osmosis process unit for producing ballast water and treatment water obtained by desalinating the sea water collected through the water collection part, and a ballast water tank for storing the ballast water produced by the forward osmosis process unit. Since the sea water is treated using a forward osmosis process, fresh water required within the ship can be supplied and the treated sea water can be used as ballast water. In addition, since waste heat and carbon dioxide generated in the ship are used to treat the sea water, the ballast water can be treated and produced in a low-cost and high efficient manner.

Abstract: An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.

Abstract: A pinned lug joint including: a first part with two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part including a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.

Abstract: An actuation system for deploying and retracting a lift assisting device of a leading edge of a wing of an aircraft including a track pivotally coupled to the lift assisting device. The track has first and second outer surfaces and side surfaces. The actuation system includes a shaft rotationally coupled within the wing of the aircraft and operable, in response to flight control signals, to deploy or retract the lift assisting device. The actuation system includes an actuator for actuating the lift assisting device, coupled to the shaft, between a retracted position to a deployed position along an arcuate path. The actuation system includes a plurality of track roller bearings rotatably contacting the first and second outer surfaces of the track to guide the track along the arcuate path. The plurality of track roller bearings includes one or more lined track roller assembly.

Abstract: Aircraft, control-by-wire systems, and controllers are provided. The aircraft includes a flight control surface and a control-by-wire system. The control-by-wire system includes an input device and a controller. The input device is configured to control the flight control surface. The controller is communicatively coupled with the input device and configured to automatically offset a neutral force position of the input device based on a deviation of the aircraft from a reference condition while the aircraft is operated in a manual flight mode.

Abstract: A main landing gear for aircraft having a fuselage, a wing and a jet engine on opposite sides of the fuselage and housed in a nacelle attached to the wing. The main landing gear includes a landing gear at each side of the wing having wheels coupled to a driving device that moves the wheels between stowed and deployed positions. The engine nacelles each include a well located laterally with respect to the jet engines and configured as a housing space for stowing the wheels of the landing gears.

Abstract: A bearing housing may comprise a cylindrical body and a groove formed in an inner surface of the cylindrical body. The groove may be configured to interface with a bearing. A tapered surface may be formed on an outer diameter of the cylindrical body. A wear plate may be disposed over the tapered surface. An elastic material may be between the tapered surface and the wear plate. The tapered surface may be conical. A length of the tapered surface may be less than half the length of the bearing housing. The tapered surface may be tapered at an angle based on a deflection angle of the piston. A second tapered surface may be formed on the outer diameter of the cylindrical body. An elastic material may be between the second tapered surface and the wear plate.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A system for operating helicopter blades with compressed air includes at least a first machine having an engine and configured for generating mechanical power to lift the helicopter; at least a second machine having a compressor and configured for generating compressed air for operating the hollow blades, the first machine being coupled with the second machine; and a rotor having a hollow shaft and an oscillating hollow head supporting the blades. The hollow shaft of the rotor internally including a conduit connecting the hollow shaft of the rotor to the hollow head. The oscillating hollow head is an elastic head and comprises an elastomeric flexible and deformable channel connecting the conduit with the blades and having a shape as at least one “V” and a number of branches equal to the number of the blades, the branches being able to guide the compressed air towards nozzles of the blades.

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: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver.

Abstract: A rocket morphing aerial vehicle has a first rocket configuration and a second aerial vehicle configuration. The rocket morphing aerial vehicle may be used to deploy an aerial vehicle at further distances faster. The rocket configuration may be used to get the aerial vehicle to its desired location, while the aerial vehicle is used for the desired task. The rocket morphing aerial vehicle may include a deceleration mechanism such that the speed of the rocket does not interfere with the deployment of the aerial vehicle.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: An axillary airfoil located as far forward as practicable on the fuselage of an airliner. During high speed cruise, the airfoil can be adjusted to provide supplemental lift to move the center of pressure forward, thereby reducing the amount of downforce needed to be produced by the vertical stabilizer. This would result in saving fuel. Spoilers mounted on the airfoils would be programmed to automatically deploy to return the center of pressure rearward whenever flight conditions require greater longitudinal stability.

Abstract: In one embodiment, multi-mode use of an aircraft cockpit is realized a processor in the aircraft determining whether the aircraft is operating in a flight mode or a non-flight mode. When operating in the non-flight mode, the processor deactivates aircraft engines and permits wireless device access to one or more aircraft systems. When operating in the flight mode, the processor enables aircraft engines and prevents wireless device access to one or more aircraft systems.

Abstract: An oven includes a housing having a first compartment enclosed on all sides and a second compartment enclosed on all sides. The first compartment includes a first back wall, a first door opposite the first back wall, the first door operable to open the first compartment; a first top wall; a first bottom wall opposite the first top wall; a first outer wall, and a first inner wall. The second compartment is adjacent the first compartment and includes a second back wall, a second door opposite the second back wall, the second door operable to open the second compartment, a second top wall, a second bottom wall opposite the second top wall, a second outer wall, and a second inner wall. An end first portion of the first inner wall opposite the first back wall is bent to form an acute angle with the first back wall.

Abstract: A personal restraint system configured for use with a seat oriented perpendicular to a direction of flight of an aircraft is provided including a lap portion and a shoulder portion. The lap portion includes a first belt having a belt buckle and a second belt having a belt connector. The first belt is arranged a first side of the seat and the second belt is arranged adjacent a second side of the seat. The belt connector removably couples to the belt buckle. A shoulder portion includes a retractable third belt having a coupling configured to selectively couple to one of the belt buckle and the belt connector. A pretensioner operably coupled to either the first belt or the second belt includes at least one sensor configured to monitor one or more aircraft conditions. Upon detection of a predetermined aircraft condition, the pretensioner applies tension to the first or second belt.

Abstract: The vehicle seat back according to the invention includes a textile assembly (30) having at least one embrittled linear zone (32, 32A, 32B) able to tear during an impact of the head of a passenger located on the seat behind the seat back considered, so as to enable rocking of this passenger's head to be continued and, at the same time, to be slowed down. Application to aircraft seats.

Abstract: A ventilation system, aircraft, and method. The ventilation system includes a first conduit in fluid communication with a first air source in the aircraft to direct a fluid flow from the first air source. The ventilation system also includes a first branch in fluid communication with the first conduit and a first outflow point, the first branch including an active air mover to move the fluid flow toward the first outflow point. The ventilation system further includes a second branch that is separate from the first branch and in fluid communication with the first conduit and a second outflow point, the second branch including a passive air mover to move the fluid flow to toward the second outflow point.

Abstract: An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

Abstract: A system and method for controlling a tail-sitter aircraft, includes determining a mode of operation for the aircraft; operating each of a large turbine engine and a small turbine engine to provide total aircraft power during hover or high-power mode of operation; and selectively providing aircraft power from the small turbine engine to a plurality of rotors during a long-range endurance cruise mode of operation.

Abstract: An actuator for a ram air turbine system includes a piston rod that is cylindrical in shape and centered about a centerline, and stow lock pawls supported by the piston rod and able to move radially. Each of the stow lock pawls has a crown with a crown radius. The actuator further includes a lock bolt extending along the centerline radially within the piston rod and configured to be axially movable within the piston rod between a stowed position and a deployed position. The actuator further includes rollers radially outward from the centerline configured to be guided by the lock bolt and a cylinder having a mating surface with a mating radius. The cylinder is positioned radially outward from the piston rod and configured to be axially movable between the stowed position and the deployed position. A ratio of the crown radius of the stow lock pawls to the mating radius of the cylinder is less than 0.98.

Abstract: A sensing orifice for an aircraft, an aircraft with such a sensing orifice and a method for assembling a sensing orifice for an aircraft are provided. The aircraft may be an airplane, a helicopter, a UAV, a drone or similar. The static sensing orifice includes a passage through an outer skin of the aircraft and a moisture protection body. The passage is designed to connect with a pressure line in the interior of the aircraft. The moisture protection body is gas-permeable and water-impermeable, and the moisture protection body is disposed such that the passage is gas-permeably and water-impermeably sealed. The method for assembling the static sensing orifice for the aircraft, includes the following steps: providing the passage through the outer skin of the aircraft for connecting to the pressure line in the interior of the aircraft, providing a gas-permeable and water-impermeable moisture protection body, and gas-permeable and water-impermeable sealing of the passage by the moisture protection body.

Abstract: A method of forming a lightning protection system for use with an aircraft is provided. The method includes selecting a configuration of at least one layer of electrically conductive material to be applied to a component of the aircraft, wherein the configuration is selected as a function of an amount of lightning protection to be provided thereto. The method also includes applying the at least one layer of electrically conductive material to the component via an additive manufacturing technique.

Abstract: A landing aid method and device for an aircraft including a unit for calculating automatically in a repetitive manner, during a final approach of the aircraft with a view to landing on a landing runway, using at least a ground speed of the aircraft, a height of the aircraft in relation to the ground, and a target vertical speed representing a vertical speed required on contact with the landing runway, a slope angle of a flight path allowing the aircraft to perform a flare, checking at least the target vertical speed on contact with the landing runway, and a unit for displaying automatically, on at least one screen of the flight deck of the aircraft, a first symbol illustrating the current slope angle of the aircraft and a second symbol illustrating the calculated slope angle.

Abstract: Embodiments of methods and apparatus for providing distributed airborne wireless communications are provided herein. In some embodiments, a communication fleet includes: an airborne communication payload subdivided into multiple payload sections; and a plurality of airborne platforms each including a payload section, wherein each airborne platform comprises an airframe, a propulsion system, a power system, and flight control electronics, wherein the propulsion system is configured to provide propulsion power and thrust to maintain level flight, ascend, descend and maneuver the airborne platform, wherein the power system provides electrical power to the propulsion system, the flight control electronics, and the payload section, and wherein the flight control electronics provide capability to control a position, speed, and flight pattern of the airborne platform.

Abstract: An exterior aircraft light unit includes a mounting structure, an LED arranged on the mounting structure, and an optical system, arranged on the mounting structure for creating an output light emission distribution of the exterior aircraft light unit. The optical system has, in a first cross-sectional plane extending through the LED, a first concave reflector and a second concave reflector, each of the first and second concave reflectors having a proximate end positioned adjacent to the mounting structure and a distal end positioned removed from the mounting structure, with the first and second concave reflectors being arranged on opposite sides of the LED in the first cross-sectional plane, and a refractive optical element arranged between the first and second concave reflectors in the first cross-sectional plane. The distal ends of both the first and second concave reflectors that curve towards each other and have back-tapered shapes.

Abstract: An exterior aircraft light unit includes a mounting structure, a plurality of first light sources arranged on the mounting structure, and a lens cover arranged over the plurality of first light sources, the lens cover having a convex shape at least in a first cross-sectional plane, wherein the plurality of first light sources are arranged in a curved pattern, with the curved pattern having the same direction of curvature as the convex shape of the lens cover in the first cross-sectional plane.

Abstract: An aircraft beacon light unit has an operating light emission distribution. The operating light emission distribution has a first light emission opening angle of at least 150° in a first cross-sectional plane, and a second light emission opening angle of at most 180° in a second cross-sectional plane orthogonal to the first cross-sectional plane. The aircraft beacon light unit is configured in such a way that it is mountable to an aircraft with the first cross-sectional plane being oriented in a vertical direction and the second cross-sectional plane being oriented in a horizontal direction, and the first light emission opening angle extends at least 75° both above and below the second cross-sectional plane.

Abstract: A coupling module provides an interface between the cabin of a passenger bridge and an aircraft. The coupling module has a projecting roof and a coupling module floor spanned by the projecting roof, with the coupling module being horizontally separable.

Abstract: A method for assembling an aircraft fuselage includes different steps. In a first step the secondary structural components and interior components are assembled to form a core structure. The core structure comprises a cabin floor, side wall panels and ceiling panels. In another step of the method a primary structure is arranged around the core structure to form a part of a fuselage.

Abstract: A processing device for the assembly of an aircraft encompasses a positioning frame, a guide device and a movable tool arm. The positioning frame can be attached to a segment of a hall floor. The guide device is movably guided on the positioning frame. The movable tool arm is attached to the guide device, and its free end exhibits a tool holder. The processing method for the assembly of aircraft encompasses the steps of providing a positioning frame on a segment of the hall floor, and guiding a guide device on the positioning arm. The guide device here exhibits a movable tool arm, and a free end of the tool arm exhibits a tool holder.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

Abstract: A system for managing momentum accumulation of a spacecraft in orbit may include a reaction wheel assembly for controlling an attitude of a body of a spacecraft, the body defining at least one face, and absorbing momentum, a plurality of arcjet thrusters coupled to the face to generate thrust, and a control processor coupled to the plurality of arcjet thrusters for controlling the thrust, wherein actuation of each arcjet thruster of the plurality of arcjet thrusters is configured to produce a net momentum accumulation in the reaction wheel assembly that is below a momentum saturation point of the reaction wheel assembly.

Abstract: A thermal protection system including a plurality of layers. A first layer includes a passive insulation material. A second layer includes a phase change insulation material. A third layer is positioned between the first layer and the second layer to separate the passive insulation material from the phase change insulation material.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

Abstract: A strapping device including a tensioner operable to apply a strap tension to a loop of wrapping strap, a friction welder operable to produce a friction weld connection at two areas of the loop of wrapping strap disposed one on top of the other, a motor operable in a first rotational direction to drive the tensioner and in a second opposite rotational direction to drive the friction welder, and a control device. The control device is configured to, in response to receiving a first designated input: (1) operate the motor in the first rotational direction to drive the tensioner until a predetermined strap tension is reached in the loop of wrapping strap; and (2) afterwards, automatically operate the motor in the second different rotational direction to drive the friction welder to produce the friction weld connection.

Abstract: The invention relates to a rigid container of foodstuff, the foodstuff comprising fist that is present in solid form. The closed container presents substantially no liquid. The invention also provides a method of manufacturing the container and apparatus for manufacturing the container.

Abstract: Method of manufacturing a package of the type formed from a single-layer or multilayer material sheet, where said package has an easy to open feature, where the sheet is shaped into the finished package having an inner side suitable to be in contact with the matter to be packaged and an outer side, comprising the following method steps: forming the film into a tube, by connecting the two side edges of the sheet longitudinally; where the connection creates a side flap on the outside of the tube or where the tube is passed over a former having a projecting fin, whereby a side flap is formed on the outside of the tube; where cross seals are provided across the tube, thereby delimiting each package between two cross seals; that perforation lines are established in said cross seals, for detaching/separating two adjacent packages; that a perforation of one material layer is established, parallel to and adjacent the side flap, extending from the perforation line towards or into the cross seal.

Abstract: The present invention relates to a labeler for applying labels to packages. The labeler can include a transport unit for transporting the packages, a label dispenser for applying a sealing label to a web-shaped rim of each of the packages, and a press-on device having a circularly movable pusher plate. The present invention also relates to a method of operating such a labeler, where the press-on device is provided for folding the sealing label around the web-shaped rim laterally to each package and for pressing the label onto the package.

Abstract: The plastic bottle (1) is filled with liquid and provided with a rigid neck (4) that defines a narrow opening (5) with an inner diameter (D5) typically inferior to 40 mm. A flexible sheet-like cover member (C), having a lower closing element and an upper reinforcing element, is provided to seal the opening A reinforcing portion (10) of the reinforcing element (C2) is directly fastened to a central portion (6) of the closing element in contact with the annular upper face (F) of the neck and reinforces this central portion. A first surface (S1) suitable for displaying label information is defined by the reinforcing portion. The outer rim (8) of the reinforcing element extends along or close to a rim (4d) of the face (F). An optional pull tab (9) forming part of the closing element (C1) and/or an extension portion forming part of the reinforcing element (C2) may be provided.

Abstract: A container (1) made of plastic material, provided with an oblate body (2) and with a bottom (3) in the extension of the body (2) at a lower end thereof, the bottom (3) including: a peripheral base (7) defining an annular standing plane (8) whose contour exhibits, along a long axis, a large dimension A, and, along a short axis perpendicular to the long axis, a small dimension A? that is strictly smaller than the large dimension, a concave arch (13) that extends from the base (7) to a central area (14); wherein the base has: along the long axis, a width C such that: 0.03 ? C A ? 0.1 along the short axis, a width C? such that: 0.05 ? C ? A ? ? 0.15 .

Abstract: A packaging system for a corrugated cardboard shipping container. The system uses two vertical compartmented inserts divided by a horizontal insert. The compartmented insert can be configured by a packer to consist of four to two rectangular compartments. The horizontal insert can be folded in half or have a quarter section folded away in order to accommodate a loading plan that requires items to protrude above the height of the bottom vertical compartmented insert. An optional diagonal divider and dunnage may be used prior to sealing the container.