Abstract: A surfboard, the rear part 1 of which is rigid and equipped for example with one or more fin boxes and other accessories such as foot strap inserts, leash inserts and or a mast box, the front part 2 of which is inflatable and equipped with a valve which permits the said inflatable part to be inflated for use and deflated after use to facilitate transport and storage.

Abstract: Embodiments of the present apparatus and method feature a permanently fixed canted keel. The apparatus and method feature tacking maneuvers which shift the sail element and reverse the direction of the hull form.

Abstract: A method for watercraft efficiency at various speeds by use of at least one adjustable trim tab with a surface by calculating by the total surface area of the planar surface and determining the surface area necessary of the planar surface of at least one trim tab, and mounting the trim tab substantially under the hull. Provided in the method is determining the overall length of the hull, determining the maximum beam of the hull, multiplying the overall length of the hull by the maximum beam, taking a resultant of the overall length and maximum beam and multiplying that resultant by a percentage in the range of about one to about three, and taking the resultant and dividing it by the number of trim tabs mounted to the hull. Adjusting the trim tab by raising or lowering the rear of the planar surface, based on speed, to achieve higher efficiency.

Abstract: The present disclosure relates to pontoon shields. The pontoon shields disclosed herein may, for example, protect pontoons from damage and/or enhance the aesthetic appearance of pontoons. The shields may be fashioned from one or more segments of resilient material configured to attach along a longitudinal aspect of a pontoon. The shields may be fashioned from a single segment, or from one or more segments configured to mate with one another. The shields may be attached to a pontoon, for example, via an adhesive, weld, and/or one or more brackets, or other mechanical means.

Abstract: A visual locator target easy to be seen from the air during the day or night to quickly locate and rescue the user in an emergency or distressed situation. The circular single-layer of bright, neon material used for this target may preferably have a diameter of 25? and be a strong, lightweight material the edge will glow-in-the-dark and inflate for water use making it easy to be seen at night for a quicker rescue. It can be used on land by laying it on the ground and securing it by using the eight anchor hook connectors. It can also be used to float in the water with the inflatable, luminescent circumference, center and cross-sections of the target which includes an inflatable chamber therein. The manual back-up air valve system requires the user to blow their breath into the air valve.

Abstract: The invention relates to a device for reducing the driving power requirement of a watercraft, comprising a flow guiding surface from which at least one first fin projects. A first end of said first fin is fixed to the flow guiding surface, and a second end of the first fin is embodied as a free end.

Abstract: An apparatus for adjusting a human propelled watercraft having a pair of flexible fins extending into the water. The invention allows the user to easily adjust the propulsion device to match the user's leg length. The invention consists of a push button mechanism that converts a vertical motion into a horizontal motion allowing a locking pin to retract and the propulsion device to be adjusted. Once an adjustment position is selected, the user releases the button and a spring reverses the motion of the pin, locking the mechanism into position.

Abstract: A thruster assembly is provided for a marine vessel, the assembly having a propeller unit (14), a motor (10) and a drive shaft (12) linking the motor (10) with the propeller unit (14) to drive the propeller unit (14). The drive shaft (12) is foldable and defines a drive path between the motor (10) and the propeller unit (14). A housing (2) locates the propeller unit (14) in a storage configuration. The motor (10) is fixed with respect to the housing (2), the housing (2) being adapted to be fixed with respect to an opening in a hull (8) of the marine vessel. An actuator (22) is operable to move the propeller unit (14) from the storage configuration to a deployment configuration in a direction from inboard to outboard, the propeller unit (14) being extended from the hull (8) for use in the deployment configuration. The propeller unit (14) is supported by a support assembly (36) which is pivotable relative to the housing (2) about a pivot axis (A).

Abstract: A marine electric power steering system includes an input assembly, a steering actuator, and a cable assembly. The input assembly is operatively connected to a steering shaft. The input assembly has a steering sensor assembly and a motor assembly. The steering actuator is disposed within a pontoon and is in communication with the steering sensor assembly. The cable assembly extends through a wall of the pontoon. The cable assembly operatively connects the steering actuator and a steering device that is pivotally mounted to the pontoon.

Abstract: An assembly is for aligning and stabilizing first and second cowl portions on a marine engine. The assembly comprises an engagement member configured to be fixed to the first cowl portion and a retainer apparatus configured to be fixed to the second cowl portion. The retainer apparatus is configured to receive the engagement member when one of the first cowl portion and second cowl portion is moved towards the other of the first cowl portion and the second cowl portion. The retainer apparatus comprises a retainer body and opposing guide members that are pivotable with respect to the retainer body. As the retainer apparatus receives the engagement member, the engagement member engages and causes the guide members to pivot with respect to the retainer body such that the engagement member becomes sandwiched between the guide members, thus aligning and stabilizing the first and second cowl portions.

Abstract: An adaptable modular power system (AMPS) is hierarchical in a number of ways. AMPS modules connect to a backplane, and one or multiple AMPS backplanes can form an AMPS domain. At the same time, the vehicle electronics is modular, with various payload boxes needing to communicate with each other. A common power and signaling cable is provided to interconnect payload boxes. A dedicated connector system is also provided so that AMPS modules may communicate, control, receive data, and supply and receive power.

Abstract: Upper anti-vibration mounts have axial lines arranged in parallel to a longitudinal center line extending in a longitudinal direction of the outboard motor body. Lower anti-vibration mounts have axial lines concentrated on one point on the longitudinal center line extending in a longitudinal direction of the outboard motor body. Meanwhile, the axial lines are inclined at the identical angle symmetrically with respect to the longitudinal center line, so that they intersect in a V-shape in front of the support shaft as seen in a plan view of the outboard motor body.

Abstract: Such a fuselage includes cross-members adapted for the formation of a floor, at least one of said cross-members including an upper part, a lower part, linkage for the lower part to the upper part, and at least one opening for the passage of systems which is delimited between the lower part and the upper part. The upper part of the cross-member is fastened to the fuselage and is dimensioned so as to bear the stresses to which said cross-member may be subjected when the aircraft remains on the ground. The lower part is fastened to the upper part so as to reinforce it such that when assembled, the upper part and the lower part are adapted to bear the stresses to which the cross-member may be subjected in flight conditions of the aircraft.

Abstract: An aircraft comprising a rear opening and a rear door to close such rear opening, wherein the rear door is attached to the fuselage of the aircraft by means of an arrangement having two links due to which the rear door can be displaced longitudinally and in elevation up to a position at the interior of the fuselage.

Abstract: The invention relates to an interior trim part (2, 3, 4, 5, 6) for the planar installation with similar interior trim parts for producing a wall covering inside an aircraft cell, wherein the interior trim part (2, 3, 4, 5, 6) can be rigidly connected to the aircraft cell. The interior trim part has a support structure (20, 21, 22, 23), wherein at least one holding position (9) is provided, which is designed to bear a load in the interior.

Abstract: A method for wing-to-fuselage integration is disclosed. The method includes attaching a fitting to a wing box assembly of an aircraft at an early stage of integration and then attaching the fitting to a stub beam attached to a fuselage panel of the aircraft at a later stage of integration. The fitting eliminates the need to attach the stub beam directly to the wing box assembly.

Abstract: Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.

Abstract: The invention relates to a flight control device for an aircraft, including a connection lever, mechanical means for limiting an angular stroke of the connection lever, first means for generating force feedback on the connection lever about said pivot axis, second means for generating force feedback on the connection lever, which means are arranged in parallel with the first means, at least one element selected from the second means and the connection lever comprising mechanical means for connecting them together temporarily, which means are arranged to be active when the connection lever is moved beyond a predetermined angular position in the angular range so that the second means are connected to the connection lever.

Abstract: An actuator for hinging a first element to a second element about a first pivot axis (A1), the actuator comprising a motor-drive device, a first mounting plate (4) connected to a body (2) of the motor-drive device, a second mounting plate (5) connected to the second element, the second mounting plate being mounted in the first mounting plate in order to pivot about the first axis, and a bush (6) mounted in the second mounting plate to pivot about a second axis (A2) perpendicular to the first axis. The motor-drive device has an outlet shaft (3) pivotable about a third axis (A3) perpendicular to the first axis and intersecting the first axis, and it is extended by a pin (7) that is pivotally received in the bush and that has a central axis (A4) intersecting the first axis and the third axis, and forming an acute angle with the third axis. An aircraft guidance assembly including such an actuator.

Abstract: A drag reduction system for an aircraft may include an air ejector having an ejection port located between an aft portion of an airfoil main element and a forward portion of a trailing edge device. The air ejector may be configured to discharge an air jet from the ejection port in such a manner that the air jet passes over the upper surface of the trailing edge device.

Abstract: There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib.

Abstract: A split winglet configured for attachment to a wing tip of a wing. The split winglet may include an upper winglet extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane. The upper winglet and the ventral fin may include tip configurations. At least one of the upper winglet tip configuration and the ventral fin tip configuration may be provided by a curved blade cap attached thereto. The curved blade cap may include a leading edge having a first curve with a first radius, and a trailing edge having a second curve with a second radius different from the first radius. The curved blade cap may also include a distal segment oblique to the first curve and the second curve.

Abstract: The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut.

Abstract: A strut assembly includes a piston and a bearing housing around the piston. The bearing housing may also comprise a groove and a tapered surface opposite the groove. A bearing may be in the groove and proximate the piston. An outer cylinder may be around the bearing housing. The angle of the tapered surface may be based on a deflection angle between the outer cylinder and the piston. A wear plate may be around the tapered surface. An elastic material may be disposed between the tapered surface and the wear plate. The bearing housing may comprise a titanium alloy. The bearing housing may be configured to flex towards the wear plate.

Abstract: A reliable reduced weight coaxial lifting system includes a reducing gear with two shafts rotating in opposite directions, upper and lower rotor hubs mounted on the respective shafts and upper and lower swashplates connected to one another, which are movable in the axial direction and are kinematically linked to guides of blades positioned on the upper and lower rotor hubs. Guides of the blades are connected to the upper swashplate by rockers mounted on a slide block located above the upper rotor hub and guides of the blades of the lower rotor hub are connected by tie rods directly to the lower swashplate. The lower swashplate is connected to control systems of a collective and a cyclical pitch and the slide block is connected to a control system of a differential pitch of the upper rotor.

Abstract: A compound aircraft having a fuselage, a main rotor, a main anti-torque device and two wings positioned on either side of the fuselage. Each wing has at least one movable flap situated at its trailing edge. The flaps can be deflected asymmetrically relative to an air stream generated in reaction to the lift of the main rotor on either side of the fuselage so as to create longitudinal aerodynamic forces in opposite directions on either side of the fuselage and consequently create an additional torque that is added to the main torque from the main anti-torque device.

Abstract: A rotary machine includes a rotatable shaft and a retaining ring coupled to, and at least partially extending about, the rotatable shaft. The rotatable shaft defines a longitudinal axis. The rotatable shaft and the retaining ring define an annular cavity. The rotatable shaft and the retaining ring each include a radially outer surface. The rotary machine also includes a monitoring system including a stationary reader-antenna positioned proximate the retaining ring and a radio frequency (RF) coupler. The RF coupler includes at least one flexible antenna band coupled to, and extending over, the radially outer surface of the retaining ring. The flexible antenna band is configured to establish RF coupling with the stationary reader-antenna. A sensor die is coupled to the flexible antenna band. The sensor die extends into the substantially annular cavity and the sensor die is also coupled to the radially outer surface of the rotatable shaft.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction.

Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

Abstract: An aerial imaging system and method of aerially capturing an image including a first unmanned aerial vehicle (UAV) and a second UAV. The first UAV includes a camera and may be configured to receive input from an operator. The second UAV may be configured to dock with and deploy from the first UAV. The second UAV includes a light configured to provide remote illumination for the camera. The light on the second UAV may be activated to illuminate a target of photography by the camera while the second UAV is flown separate from the first UAV.

Abstract: A drone includes a plurality of rotors disposed at and around a base and operable to fly and steer the drone. At least one net launcher is disposed at the base and is operable to launch a net toward a target object. A control is responsive to a signal indicative of a detected target object, and the control, responsive to such a signal, is operable to aim the net launcher toward the target object and to launch the net toward the target object.

Abstract: An air cushion cargo shuttle includes a frame having a channel, an air curtain disposed within the channel of the frame, an air blower configured to blow air into an air volume beneath the air cushion cargo shuttle, and an air cushion formed by the air curtain configured to maintain the air volume.

Abstract: Described are seat track fittings (100) with a stud (102) having a spacer (104) separated from a lower flange (106), and a locking mechanism (110). The locking mechanism includes an elastic fitting (112) having an upper arm (116a) and a lower arm (116b) connected by a resilient member (120). An end of the upper arm and an end the lower arm are coupled to the stud, with the end of the upper arm positioned above the spacer, and the end of the lower arm positioned above the lower flange. An activation mechanism (114) is coupled to the elastic fitting to transition the seat track fitting between unloaded, unlocked, and locked positions.

Abstract: A novel crash-resistant aircraft includes a fuselage and an aircraft base connected together via a movable fastener, and said fuselage comprises a cockpit, a cabin and an empennage. The aircraft base comprises a bellyhold cargo bay, a fuel tank, an undercarriage, a power unit and wings. The empennage is also connected to the tail end of said fuselage via a movable fastener. A crash-resistant propeller system capable of bringing said fuselage upward is set up at the top of said cabin, a crash-resistant recoil devices set up beneath said cabin. The crash-resistant aircraft also comprises a control system disposed in said cockpit, and when said aircraft is in an accident in midair, said control system releases said movable fastener to abandon said aircraft base and said empennage. Also disclosed is a crash-resistant operation method of the crash-resistant aircraft.

Abstract: A method of driving a rotorcraft rotor (1, 2) at variable controlled speeds. Starting from a required speed (Nr), a setpoint for total power (Pt) is calculated while taking account of an anticipated power (Pf) to be delivered by the power plant (3) for driving the main rotor (1) at the required speed (Nr), and while taking account of a power surplus (S) relating to progressive power needs to be delivered from a current power (Pc) for driving the main rotor (1) at a current speed (V) of rotation to an anticipated power (Pf) for driving the main rotor (1) at the required speed (Nr). By way of example, account may be taken at least of the acceleration or conversely of the deceleration of the main rotor (1) between the current speed (V) and the required speed (Nr), or indeed account may be taken of the flight circumstance of the rotorcraft 30 determining the calculated required speed (Nr).

Abstract: Systems and methods for stabilizing an aircraft in response to a yaw movement are provided. In one embodiment, a method includes detecting a yaw movement of the aircraft. The yaw movement can cause a front portion of the aircraft to move towards a first side of the aircraft. The method can further include, in response to the yaw movement, initiating a trim process resulting in a thrust differential. The trim process can include increasing thrust in one or more engines on the first side of the aircraft and decreasing thrust in one or more engines on a second side of the aircraft. The method can include controlling the trim process based at least in part on a detected yaw movement of the aircraft.

Abstract: A system and method for displaying standby instrument information is disclosed. The touch-screen instrument panel system for a vehicle has a touch-screen information panel display configured to display vehicle operation information received from a computing system and a standby instrument display that is secured to an area located behind the information panel display. The standby instrument display is hidden from view when the information panel display is in a powered state but is in full view when the information panel display is in an unpowered state.

Abstract: Methods and apparatus for determining seatbelt status are disclosed. An example seatbelt system for a mass transit vehicle includes a first seatbelt of a first seat that includes a first buckle and a first magnetically-responsive switch to detect a first tongue when the first seatbelt is in a fastened position. The example apparatus includes a second seatbelt of a second seat that includes a second buckle and a second magnetically-responsive switch to detect a second tongue when the second seatbelt is in the fastened position. The example apparatus includes a remote monitoring unit to indicate, when the first seat is occupied, if the first seatbelt is in the fastened positioned or an unfastened position. The remote monitoring unit is to indicate, when the second seat is occupied, if the second seatbelt is in the fastened positioned or the unfastened position.

Abstract: An autonomous cargo handling system is provided. The autonomous cargo handling system may comprise one or more sensing agents in electronic communication with each other. One or more of the sensing agents may be configured to monitor a sensing zone in a cargo deck to detect objects traveling through the sensing zone. In response to detecting an object, one or more sensing agents may determine an object property based on the detected object. One or more sensing agents may generate an object model based on the determined object properties. The sensing agents may also determine whether the detected object is a unit load device (ULD) or a non-ULD object based on the object property and/or the object model.

Abstract: Devices and methods for stabilizing a structural component are provided. The devices may include a main body component, a pair of opposed stabilization feet engageable with opposed regions of the structural component, a pair of coaxially disposed and reciprocal rectilinearly movable support shafts coupling the stabilization feet to the main body component, and an actuator assembly for rectilinearly moving the support shafts opposite to one another which in turn moves the stabilization feet between retracted and extended positions relative to the main body component. In use, the device may be positioned between opposed flanges of a structural component so as to stabilize the component and facilitate automated assembly processes.

Abstract: A landing gear assembly may include a first wheel and a second wheel, a first wheel sensor coupled to the first wheel and a second wheel sensor coupled to the second wheel, and a controller coupled to the first wheel sensor and the second wheel sensor. A tangible, non-transitory memory may have instructions for detecting a dragging brake. The controller may perform operations including receiving data from the first wheel sensor and the second wheel sensor, calculating a wheel speed characteristic for each of the first wheel and the second wheel based on the data, identifying a lowest value for the wheel speed characteristic, determining a moving average for the wheel speed characteristic, comparing the lowest value to the moving average, and whether the lowest value for the wheel speed characteristic indicates a dragging brake.

Abstract: A method for stationing a satellite comprises a transfer phase, during which the satellite moves on an elliptical geosynchronous orbit, the orbit being deformed progressively by application of a thrust by electrical or hybrid electrical-chemical propulsion to bring it closer to a geostationary orbit. The transfer step comprises a substep during which, during a plurality of revolutions of the satellite, the thrust is stopped for a fraction of orbital period and tests of a telecommunications payload of the satellite are performed in the absence of thrust.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Various embodiments of the present invention include assemblies and methods for minimizing the amplitude of attitude jitter. In one embodiment, a flywheel assembly for reducing the amplitude of attitude jitter is provided. The flywheel assembly includes a first flywheel, a second flywheel, and a third flywheel. The first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another. Each flywheel is configured to be independently controlled in order to manipulate the phase difference therebetween.

Abstract: A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form.

Abstract: A solar panel assembly for a spacecraft includes a bracket and first and second booms each having a first end secured to the bracket and a second end extending away from the bracket. Each boom is formed from a plurality of tubes that telescope between a stowed condition nested within one another and a deployed condition aligned end-to-end with one another. A solar panel is secured to the first and second booms for receiving solar energy and converting the solar energy to electrical power. The solar panel has a stowed condition collapsed between the first and second booms and a deployed condition extending in a plane between the first and second booms.

Abstract: A system for filling a container with relatively long thin tubes that are delivered on a tube conveyor. The system has a generally tubular-shaped insert with an at least partially open top and an open bottom, the insert sized and shaped to fit into the container and defining a width that is slightly larger than the length of the tubes and an insert holder that is adapted to engage the insert to hold the insert in place. There is a lift system that moves the container between an engaged position in which the container is located over the insert and a disengaged position in which the container is free from the insert, and movable clamps adapted to be moved between an engaged position in which they hold the container in position relative to the insert and a disengaged position in which the container can be moved relative to the insert. A pivot system pivots the insert holder about a pivot axis that is generally parallel to the longitudinal axes of the tubes.

Abstract: A lunch box assembly having a main housing having a lid rotatably, hingedly attached to a base to provide access to an opened interior of one or more compartments is disclosed. The lid can have ferrously magnetic material and recesses to accept magnets. The magnets can be shaped to fit the recesses. The base can have compartments aligned with corresponding compartments in the lid. The base and the lid can form one or more closed food storage compartments that separate the contents from the neighboring compartments. A latch on the base and lid can produce a clamping force on a small lidded container or containers placed in one or more of the compartments. The clamping force can clamp the lidded container closed and prevent leakage of fluids in the container.

Abstract: A method and a device for handling test tubes in a laboratory automation system are presented. During the handling, an open end of the test tube is covered by a residue-free removable, flat cover element forced against the open end of the test tube.