Abstract: The invention relates to a system (1) for binding a shoe (2) to a foot rest (3) of a towing boat, said shoe (2) having a sole (21) and said foot rest (3) being likeable to a plate having an underside (9) and a top surface (8). The main feature of a binding system according to the invention is that it comprises at least one mobile step (6) projecting from the top surface (8) and a rigid actuating lever (4) projecting from the underside (9), and in that said lever (4) is connected to said at least one stop (6) in such a way that moment of said lever (4) causes said at least one stop (6) to move between a deployed position in which it becomes lodged in a recess (22) in the sole (21), and a retracted position in which it leaves said recess (22) and allows the shoe (2) to be detached them the foot rest (3).

Abstract: A drive system pivot assembly for a personal user powered watercraft is provided. The drive system pivot assembly pivots a drive system between a deployed position and a parked position. The drive system pivot assembly includes a catch arrangement for securing the drive system pivot assembly in the parked position.

Abstract: A method of installing interior modules to support structures in an aircraft fuselage comprises attaching fixed ends of a plurality of tie rods to the support structures; and determining installation length of the tie rods, installation spacing between free ends of the tie rods, and installation orientation of the tie rods prior to positioning the interior module for installation. The method further comprises securing tie rod holding fixtures to the tie rods to hold the spacing and orientation at or near final configuration to facilitate installation of the interior modules.

Abstract: A structure for fastening components of interior equipment in the passenger compartment of an airplane. The fastening structure contains a fastener produced on the fuselage; suspension elements (2) immovably connected to the fastener, and at least one system support (1) running in the longitudinal direction of the fuselage, connected to the suspension elements (2). The suspension elements (2) include at least one first suspension element (9) and at least one second suspension element (10, 11), wherein each of the first suspension elements is rigidly connected to the system support, and each of the second suspension elements forms with the system support a sliding connection, so that the system support is able to slide relative to these second suspension elements along the longitudinal axis of the airplane fuselage. The sliding capability of the system support relative to the second suspension elements substantially reduces the load on the bulkhead in the longitudinal direction.

Abstract: The invention relates to a single-piece stringer for an aeronautic structure, the stringer comprising a single-piece body including at least one hollow longitudinal portion so as to define an outer enclosure, said outer enclosure including a plurality of openings.

Abstract: The invention relates to an aircraft structure, the aircraft structure comprising a first component and a second component. A fastening device fastens the first component to the second component, wherein the fastening device comprises a clamping member, and a fastening member. The fastening member has a longitudinal axis, and the clamping member is associated with the first component such that the clamping member is movable in a first direction and is fixed in position in a second direction, the first direction being parallel to the longitudinal axis of the fastener, wherein the fastener extends through the second component into engagement with the clamping member and holds the clamping member against the second component. The fastening device may hold the first component and second component in a fixed position relative to one another, in at least one direction, without applying a clamping force between the first component and second component.

Abstract: A blade for a turbine engine propeller, in particular a propfan engine, comprising a protruding part on the leading edge thereof, wherein said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

Abstract: A propeller which can be folded and stowed in compact form and then deployed for powered flight is disclosed. The deployable propeller has two or more blades, and each blade is composed of multiple segments which are disengaged when stowed and then interlock when deployed to form an efficient blade. The segmented deployable propeller retains all effective area to the spinner radius.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: The present invention provides a multi-rotor flying object including: a body; a plurality of rotor units each including a propeller and a power unit for driving the propeller; and a steering unit including a connection member connecting the plurality of rotor units to each other and an actuator installed on the body and activating the connection member to allow the plurality of rotor units to be simultaneously inclined at the same angle with respect to the body.

Abstract: An aircraft spring assembly having a spring, an end fitting including a spring engagement formation arranged to be mechanically coupled to an end region of the spring and a coupling formation for coupling the spring assembly to an aircraft anchor point. The coupling formation includes a load bearing surface via which loads from the anchor point can be transmitted into the spring assembly. The assembly further includes an integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring.

Abstract: Aircraft landing gear comprising a locking assembly including a pair of spaced-apart bearing pads and a lock member. The lock member is moveable between a locked position in which it engages the bearing pads to prevent pivotal movement of a steerable axle, and an unlocked position in which the member is disengaged from the bearing pads such that movement of the axle can occur. The lock member has a guide surface on either side for guiding the member and bearing pads into alignment during movement of the member from the unlocked to the locked position. The guide surface comprises a first inclined portion for moving the member towards alignment with the bearing pads and a second inclined portion, spaced apart from the first portion, for moving the member into alignment with the bearing pads such that the member and bearing pads are aligned in a movement comprising two stages.

Abstract: A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

Abstract: An aircraft is provided, which comprises a support structure and at least four lift rotors. Each of the lift rotors is attached to the support structure and comprises at least one propeller. The lift rotors are constituted such that a rotational plane, in which the at least one propeller of the lift rotor rotates, is tilted with respect to a plane formed by the support structure.

Abstract: A disc-shaped aircraft including an airfoil having a convex upper surface and a planar lower surface with the edges of the surfaces meeting at the periphery of the disc and having a plurality of rotational mini turbine jets affixed sequentially at the edge of the circumference of the disc, the turbine jets effecting vertical, horizontal, and directional thrust under computer and pilot control. Stable flight is maintained by an internal gyroscopic counter-rotating rotor blade system, individual control of the turbine jets, and a series of retractable flaps.

Abstract: The kite frame assembly contains a kite frame, a number of limiting elements, and a number of fastening elements. The kite frame contains a main stick, a number of connection elements movably configured along the main stick, and a number of auxiliary sticks joined to the main stick. The limiting elements are movably configured along the main stick; and the fastening elements are fixedly configured along the main stick. Each connection element is sandwiched between a pair of limiting elements, which in turn sandwiched between a pair of fastening elements. As such, each connection element is movably limited to an appropriate position range along the main stick and enhanced flexibility and convenience is achieved when assembling a kite.

Abstract: A system including an aerial vehicle having an airframe and a power source onboard the aerial vehicle, wherein the aerial vehicle includes a landing gear structure having a first electrical contact and a second electrical contact, and a charging station having a first electrical contact and a second electrical contact, wherein the aerial vehicle is programmed to dock with the charging station when the power source is in need of recharging, the docking being a mechanical engagement between the first electrical contact and the second electrical contact of the aerial vehicle with the first electrical contact and the second electrical contact of the charging station is provided. A method for continuous surveillance utilizing the aerial vehicles and charging stations is also provided.

Abstract: Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

Abstract: A passenger control unit is provided that may include a push-button, power assembly, and control and communication circuitry. The push-button may be for control of a passenger service unit (PSU) onboard a passenger vehicle, and may also generate mechanical energy when pushed. The power assembly may convert the mechanical energy to electrical energy, and store the electrical energy, solely from which the control and communication circuitry may be powered. The control and communication circuitry may include a microprocessor and a communications interface. The microprocessor may receive an indication when the push-button is pushed, and generate an instruction to control the PSU in response thereto. And the communications interface wirelessly transmit the instruction to a control unit configured to effect control of the PSU based thereon.

Abstract: Disclosed is a removable seat divider for placement in a seat. The removable seat divider includes a vertical structure configured to be placed on the seat along an approximate center of the seat. The vertical structure includes a first outer surface, second outer surface, top, and back portion, where the back portion of the vertical structure is configured to be placed adjacent to a back portion of the seat. The removable seat divider also includes a cavity located adjacent to the back portion, where the cavity connects the first outer surface to the second outer surface, and the cavity is configured to pass a seat belt through the cavity. The base back portion is configured to produce a restraining force against the seat that is proportional to a tension on the seat belt that passes through the cavity.

Abstract: An armrest assembly for a seat including a static frame member, an armrest pivotally attached at one end to the static frame member, and an armrest pivot guard pivotally attached at one end to the armrest or the static frame member. The armrest pivot guard moves with armrest motion to conceal and/or maintain coverage of a pinch point near an attachment point of the armrest to the static frame member.

Abstract: An environmental control system (ECS) pack is provided including a primary heat exchanger and a secondary heat exchanger. An air cycle machine is arranged in fluid communication with at least one of the primary and second heat exchanger. The air cycle machine includes a compressor and a plurality of turbines. Discharged cabin air is supplied to at least one of the plurality of turbines to operate the compressor.

Abstract: An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a first gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

Abstract: A deicer boot includes a plurality of first elastomer fibers and a first carbon allotrope material selected from the group consisting of carbon nanotubes, graphene, graphite and carbon black. The first carbon allotrope material is aligned with one of the first elastomer fibers. The deicer boot also includes a plurality of second elastomer fibers and a second carbon allotrope material selected from the group consisting of carbon nanotubes, graphene, graphite and carbon black. The second carbon allotrope material is aligned with one of the second elastomer fibers. The second elastomer fibers are different from the first elastomer fibers.

Abstract: Nacelles are provided having a tubular casing, open at its opposite axial ends, with an inner wall and an outer wall which are connected to each other at the front end along a leading edge and at the rear end along a trailing edge and which enclose, together with the leading edge and the trailing edge, a cavity. To prevent the formation of ice at least in the zone of the leading edge of the nacelle, a separating member made of porous material is arranged inside the cavity to divide the cavity into an inner cavity, between the inner wall and the porous separating member, and an outer cavity, between the outer wall and the porous separating member, and to put the inner cavity in fluid communication with the outer cavity only in a front zone of the cavity in contact with the leading edge, and a two-phase fluid is contained in the cavity.

Abstract: A deicer includes an aircraft structure and an outer layer with a sheet having a brittle point lower than ?40° C. (?40° F.). The sheet includes a polyether urethane elastomer. A deicer includes an aircraft structure and an outer elastomer layer. The outer elastomer layer includes a non-woven fabric having polyether urethane fibers and one of (1) a carbon allotrope material aligned with at least one of the polyether urethane fibers and (2) a polyester urethane composition located on a portion of the non-woven fabric. A method of forming a layer of a deicer boot includes forming a polyether urethane elastomer sheet having a brittle point lower than ?40° C. (?40° F.) and incorporating the polyether urethane elastomer sheet onto an aircraft structure.

Abstract: A deicer boot includes an aircraft structure and an outer layer. The outer layer includes a plurality of elastomer fibers and a carbon allotrope material. The carbon allotrope material is aligned with at least one elastomer fiber belonging to the plurality of elastomer fibers. A method of forming a layer of a deicer boot includes aligning a carbon allotrope material with a first elastomer fiber, joining the first elastomer fiber with a plurality of additional elastomer fibers to form a non-woven fiber fabric, and incorporating the non-woven fiber fabric into a sheet.

Abstract: An unmanned aerial vehicle includes a closely integrated emergency recovery and operation systems for an unmanned aerial vehicle with built-in levels of redundancy and independence to maximize the likelihood of a controlled velocity landing. The unmanned aerial vehicle may include multiple processors and multiple state estimating modules such as inertial measurement units to independently determine the operational and error status of the unmanned aerial vehicle. Base on predictive or projected computations, the emergency recovery system may determine a suitable time for a recovery action, such as parachute deployment, and execute the recovery action.

Abstract: An adaptive aircraft engine including a first, inner bypass duct inside a core engine of the aircraft engine and a second, outer bypass duct at least partially surrounding the first bypass duct, and adaption means, in particular adjustable nozzles for altering a flowed-through cross-section of the core engine with the first bypass duct and for altering the flowed-through cross-section of the second bypass duct depending on the flying speed. An aircraft having at least one adaptive aircraft engine is also provided.

Abstract: A load bearing element for attachment of a heat generating unit to a heat sensitive supporting structure, wherein said load bearing element includes at least one body integrally formed by additive layer manufacturing, ALM. The body is adapted to provide a controlled heat transfer from said heat generating unit to said heat sensitive supporting structure.

Abstract: An apparatus and method according to one or more embodiments are provided for a latching mechanism. The latching mechanism may be implemented, for example, as a positive lock latching mechanism that provides a positive indication when a latch is not engaged. In one example, an apparatus includes a latch arm comprising a slotted hole and a latch hook configured to engage a pin. The latch includes a bifold handle coupled to the latch arm, the bifold handle comprising a first handle portion and a handle extension portion, wherein the first handle portion comprises a lock hook configured to translate through the slotted hole to engage the pin and the handle extension portion is configured to move away from the first handle portion when the lock hook is not engaged with the pin. Additional systems and methods are also provided.

Abstract: A fuel delivery system is provided for filling a fuel tank with a prescribed volume of fuel. The delivery system includes a fuel tank, a piezoelectrically-actuated fill control valve for controlling flow of fuel into the fuel tank, and a controller for controlling the closure rate of the fill control valve to accurately control the volume of fuel provided to the fuel tank. The controller receives an input corresponding to a measured volume of flow through the system and allows for closure of the fill valve at variable closure rates. The fill control valve is piezoelectrically-actuated and controlled by the controller such that each successive variable closure rate is relatively slower than the previous closure rate. In this way impact loads from shutting off the fill control valve are minimized to achieve a fill volume as close as possible to the prescribed volume.

Abstract: A method of determining the longitudinal air speed VairX and the longitudinal ground speed VsolX of a rotary wing aircraft depending on the exposure of the aircraft to the wind, the aircraft flying at a speed of advance Va. The method making it possible to determine characteristic speed curves for the aircraft depending on the longitudinal speed of the relative wind to which the aircraft is subjected, and then during a flight and depending on the actions of the pilot of the aircraft, to deduce the longitudinal ground speed VsolX and the longitudinal air speed VairX to be applied to the aircraft depending on variations in the longitudinal speed of the relative wind to which the aircraft is subjected.

Abstract: An activation device comprising a computation unit configured to compute a stall margin of the aircraft, an information reception unit configured to receive information indicating if an automatic angle-of-attack protection system of the aircraft is active or inactive, and an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive.

Abstract: Despite pilot training and current safety systems, aircraft accidents continue to occur. It is recognized herein that existing approaches to preventing aircraft accidents lack capabilities. A predictive aircraft recovery control unit can receive flight data from the plurality of data nodes. The flight data can be indicative of at least a speed of the aircraft and a position of the aircraft. In some cases, based on the flight data, the predictive aircraft recovery control unit can determine that the aircraft will enter a stall condition. Furthermore, based on the flight data, the predictive aircraft recovery control unit can determine a time period that will elapse before the aircraft enters the stall condition. In response to determining that the aircraft will enter the stall condition after the time period elapses, the predictive aircraft recovery control until can trigger a recovery sequence before the aircraft enters the stall condition.

Abstract: A method includes receiving first vehicle data from a sensor on a vehicle at one or more processors executing a first software module. The method includes determining a risk value, a confidence value associated with whether the first vehicle data matches a validated vehicle state, and a benefit value associated with providing the first vehicle data to a second software module. The method includes calculating a health score associated with the first vehicle data based on the risk value, the confidence value, and the benefit value. The method includes, in response to the health score meeting a threshold value, determining whether the first vehicle data is internally consistent, externally consistent, and stable over time. The method further includes, in response to the first vehicle data being internally consistent, externally consistent, and stable over time, providing the first vehicle data to a vehicle flight control system.

Abstract: An avionics display system is provided that modifies the appearance of an uplink message when the uplink message is affected by a flight information message. The avionics display system comprises a display device; and a processing device configured to: determine whether a flight information message affects an uplink message; and modify the displayed appearance of the uplink message on a display device when the uplink message is affected by the flight information message; wherein the display device is communicatively coupled to the processing device and located onboard an aircraft.

Abstract: A wearable electronic display system detects aircraft flight related conditions, compares the detected flight related conditions with rules or procedures, retrieves flight condition information relating to phase of flight, and displays small amounts of contextually relevant flight condition information on a display screen.

Abstract: Flight deck systems are provided for integrating braking action information with flight deck runway functions. In one embodiment, the flight deck system includes a cockpit display device on which an airport display, such as a two dimensional or three dimensional Airport Moving Map, is generated. A controller is coupled to the cockpit display device and configured to produce a braking action graphic on the airport display indicative of the current braking action of a first runway approached for usage by the aircraft. The controller may determine the current braking action of the runway from braking action information received over a datalink. Further, in certain embodiments, the controller can assign the current braking action of the runway to a predetermined braking action category and produce the braking action graphic to visually identify the assigned braking action category.

Abstract: A Light Emitting Diode (LED) light for an aircraft includes a hollow cylindrical body, a plurality of LEDs mounted in the hollow body, and at least one reflector to receive light beams emitted by the LEDs and configured to direct the light beams in a lighting direction of the LED light. The LEDs are mounted on a cylindrical support and disposed radially in the cylindrical body, and the cylindrical support has a polygonal contour.

Abstract: A helicopter dolly includes a platform defining a helicopter landing area, a plurality of rollers connected to the platform such that a vertical clearance is defined between the platform and the ground and a plurality of safety panels movably connected to edges of the platform so as to be movable relative thereto between raised and lowered positions. The safety panels cover the vertical clearance in the lowered position. A method of using a helicopter dolly includes arranging a helicopter dolly for a helicopter landing, moving a plurality of safety panels and a plurality of corner members to cover a vertical clearance defined between a platform and the ground and moving the plurality of safety panels and the plurality of corner members to uncover the vertical clearance after the helicopter landing.

Abstract: An unmanned aerial vehicle launch tube that has at least one layer of prepeg substrate disposed about an aperture to form a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Abstract: Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. The shuttle is detachable from the motor-driven tape, such that stoppage of the tape can be separate from stoppage of the shuttle. Embodiments further provide a secondary arrestment strap. Further embodiments provide an anti-rollback latch system.

Abstract: In one embodiment, a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly are affixed to a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

Abstract: A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.

Abstract: An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

Abstract: An energy absorbing restraint device for a clamp system is disclosed. The clamp system can include a releasable clamp having first and second ends, a securing mechanism connecting the ends and facilitating clamping and release of the clamp, and a restraint device for containing the clamp after release. An energy absorbing member supported about the restraint device can be configured to interface with the releasable clamp to dissipate the impact energy of the releasable clamp and decrease the magnitude of impact shock about the restraint device as created by the release of the clamp.

Abstract: A parameter of an actual spacecraft can be estimated based on a spectroscopic image of an emission from an atomic or molecular product of an interaction between an atmospheric gas and an atomic or molecular species in a plume from the actual spacecraft. The actual spacecraft can be characterized by a set of values of at least N parameters. An N-dimensional lookup table can store information about a plurality of simulated emissions, each being from the atomic or molecular product of a simulated interaction between the atmospheric gas and the atomic or molecular species in a plume from a simulated spacecraft characterized by a corresponding set of values of the N parameters. A simulated emission can be selected based on comparisons between the information about the simulated emissions and the spectroscopic image. A value of at least one of the N parameters of the actual spacecraft can be estimated based on the selected simulated emission.

Abstract: Described is a unit for releasing product for extraction or infusion beverages in containers (2) forming single-use capsules (3) comprising: at least one seat (S1) for containing a predetermined dose (33) of product having side walls; a device (6) for feeding the product in the containing seat (S1) to define the dose (33); a device (70) for compressing the product in the containing seat (S1); a device (10) for moving the seat (S1) along a closed path (PS); a device (71) for ejecting the dose from the containing seat (S1); a unit (15) for controlling and operating the compacting device (70) and the ejection device (71); the control and operating unit (15) being configured for controlling the compacting device (70) with a force such as to produce a compression which causes a coupling of the dose (33) with the side walls of the containing seat (S1) which prevents, in the operating condition of the unit, the escape of the dose from the containing seat (S1) in the absence of actions mechanical for pushing on the d