Abstract: An aircraft includes a partition wall for supporting monuments such as lavatories and galleys. The partition wall may support a large majority of the weight of the monuments such that the flooring of the aircraft is relieved of the force from various monuments. Additionally, the partition wall may be used to support the fuselage of the aircraft.

Abstract: A pressure bulkhead for a pressurized cabin of an aerospace craft includes: a pressure wall and a frame for connecting the pressure wall to the aerospace craft; wherein the frame is connected to the pressure wall; wherein the pressure wall has: a core layer; and a first covering layer and a second covering layer; wherein the core layer is arranged between the first covering layer and the second covering layer; and wherein the core layer comprises an auxetic foam. Such a pressure bulkhead has increased stiffness, thus ensuring that smaller bending deformations and lower stresses occur. Hence costs can be saved, and the volume of the pressurized cabin which can be made available to the crew and passengers is maximized.

Abstract: An electrical and electronic bay for an aircraft includes a central area forming a free space, a peripheral side area provided for the arrangement of supporting structures and being placed around said central area, and a lower area placed below the central and peripheral side areas and in which the access opening is placed in said central area. Such an electrical and electronic bay is used in particular to optimize the areas dedicated to the incorporation of electronic equipment in aircraft.

Abstract: A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises at least one lower skin and stringers integrally formed with the lower skin, and frame segments extending crosswise relative to the stringers. Shear-ties are co-cured or co-bonded with the lower skin and extend crosswise relative to the stringers. Frame segments are fastened to the shear-ties, such that the frame segments are distanced from the lower skin. An aircraft rear fuselage section comprises an upper fuselage shell and the described lower fuselage shell. The upper fuselage shell has an upper skin reinforced with omega-shaped stringers, and the lower shell has a lower skin reinforced with T-shaped stringers.

Abstract: A nose section of an aircraft comprising a centered flight deck, making it possible to offer a direct forward field of view towards the outside of the aircraft, the forward visibility of the pilot towards the outside taking priority, and an indirect lateral field of view afforded by image displays displaying images representing the lateral environment of the centered pilot and obtained from an image capturing device.

Abstract: A porthole, a porthole plug in a vehicle, and an aircraft with portholes are provided. The porthole includes an opaque plug with an aperture therethrough.

Abstract: The adjustable fuselage location method is based on the combined use of slots under fuselage longerons, saddles between fuselage and wing, straps, brackets, thread poles and nuts. Saddles installed under the fuselage provide an interface between the fuselage and wing. Straps wrap around the brackets inside fuselage longerons, saddles and wing box for fastening the wing to the fuselage. Thread poles are affixed on the brackets for guiding the traveling of fuselage in longitudinal direction. By turning the nuts on the poles, fuselage can be relocated on the wing. These adjusting mechanisms can be hided inside the longerons of fuselage and manipulated from inside of the fuselage.

Abstract: A sealed bottom in the frame of a cockpit with centered pilot is disclosed for increasing the bulk inside the radome and making it possible to improve the optimization of the volumes. The sealed bottom includes a semi-cylindrical central part having four edges that are parallel in pairs, two curved edges, and two straight edges and a planar peripheral part extending at least partially around the central part. The peripheral part (22) is located in the plane of the straight edges of the central part and linked thereto. This configuration will allow to free up space to increase the number of passengers or reduce the size of the aircraft.

Abstract: Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Abstract: A fluid foil has a main fixed portion and a tip portion movably mounted at a tip end of the main fixed portion. The main fixed portion has an upper surface and a lower surface, and the tip portion has an upper surface and a lower surface. The fluid foil is operable in: a) a first configuration in which the upper surface of the tip portion is angled downwardly with respect to the upper surface of the main fixed portion; and b) a second configuration in which the tip portion is rotated upwardly with respect to the first configuration such that the upper surface of the tip portion and the upper surface of the main fixed portion are substantially continuous surfaces. The movement of the tip portion with respect to the main fixed portion is exclusively passively actuated by movement of the foil with respect to a surrounding fluid.

Abstract: This disclosure provides construction variants of a cruise miniflap of an aircraft wing that is added to trailing edge flap of an aircraft wing and can be used for improving the aerodynamic properties of an aircraft. In the rear edge of the cruise miniflap there is a cavity with a height of up to 1% of the wing chord.

Abstract: Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced.

Abstract: A lift fan includes a stator which is configured to output a magnetic field. The lift fan also includes a first housing which in turn includes a blade, a second housing, and a magnet array. The magnet array is coupled to either the first housing or the second housing and the housing, which is coupled to the magnet array, rotates in response to the magnet array responding magnetically to the magnetic field output by the stator.

Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A rotor unit is disclosed. The rotor unit includes a hub and a stacked rotor blade. The hub is configured to rotate about an axis in a first rotation direction. The stacked rotor blade is rotatable about the axis and further includes a first blade element and a second blade element. The first blade element has a first leading edge and the second blade element has a second leading edge. The blade elements are arranged in a stacked configuration. A leading edge of the stacked rotor blade is formed by at least a portion of the first leading edge of the first blade element as well as at least as portion of the second leading edge of the second blade element. In some embodiments, the rotor unit is coupled to an unmanned aerial vehicle.

Abstract: A payload transport aircraft that includes a nacelle including a cockpit, a first wing extending in a first direction from the nacelle and a second wing extending in a second direction from an opposing side of the nacelle. The aircraft also includes a first pair of wheel-struts extending between the first wing and a first set of corresponding wheels and a second pair of wheel-struts extending between the second wing and a second set of corresponding wheels. Each member in the pair of wheel-struts is connected by a wheel-strut stabilizing segmented cross-bar having a rear segment and a front segment joined at a disconnection point by one or more coil-springs, which can be tension springs resistant to stretching mounted to each segment through the use of spring mounting-posts fitted into each segment and protected using a cover that can be removable and transparent for quick visual inspection.

Abstract: An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and a flexible vessel actuator configured to radially enlarge the tube at a region for folding.

Abstract: A non jamming shrink latch is provided and may comprise a cradle, a first rocker arm, a first inboard pivot, and a first outboard pivot, wherein the first inboard pivot is coupled to the first rocker arm at a first end and the first outboard pivot is coupled to the first rocker arm at a second end opposite the first end, and wherein the cradle is coupled to the first outboard pivot. In various embodiments, a non jamming shrink latch may further comprise a second rocker arm coupled to the cradle at a second outboard pivot and a second inboard pivot coupled to the second rocker arm opposite the second outboard pivot.

Abstract: A latch assembly for a shock strut may comprise a first linkage coupled to a strut cylinder and a shrink piston of the shock strut. A second linkage may be coupled to the strut cylinder. The second linkage may be configured to rotate the first linkage in response to the shock strut translating between a landing gear up position and a landing gear down position.

Abstract: A landing gear controller for an aircraft is configured to: detect an extension time for a landing gear, and if the detected extension time meets a predetermined criterion, provide a warning signal to indicate potential failure of a landing gear uplock hook. The landing gear controller may be in a landing gear system.

Abstract: A technique of controlling tonal noises produced by an unmanned aerial vehicle (UAV) includes generating thrust with a plurality of rotor units mounted to the UAV to propel the UAV into flight. Each of the rotor units includes a bladed rotor. A rotation rate or a phase delay of at least one of the rotor units is adjusted relative to another of the rotor units. The adjustment causes a spread in the tonal noises generated by the rotor units.

Abstract: A yoke split into separate, individual yoke arms permit rotor blade fold about inboard yoke arm bolts in a rotor blade assembly for rotorcraft and tiltrotor aircraft. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard CF bearing and the yoke tip. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: An intermeshing rotary-wing aircraft comprises a first rotary blade portion including a first blade and a second blade, a second rotary blade portion including a third blade and a fourth blade, a first shaft and a second shaft that transmit power to the first rotary portion and the second rotary portion and are symmetrically positioned at a predetermined angle, a first swash plate portion for controlling the first blade and the second blade, and a second swash plate portion for controlling the third blade and the fourth blade, wherein the first swash plate is coupled to three linkages, in which the coupled positions are located at the vertices of an equilateral triangle, the second swash plate has the same shape as the first swash plate, and the two equilateral triangles of the first swash plate and the second swash plate are star-shaped when horizontally moved and overlapped.

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

Abstract: A single tow point box kite is presented that includes a single piece fabric canopy having a pair of sails connected via sleeves. The pair of sails are maintained in a drum-tight fashion to form a quadrangular configuration via a demountable frame that includes a plurality of spars projecting between the sails and through respective sleeves, with respective opposite extremities of the spars received in respective pockets of the fabric canopy, and struts projecting between pairs of spars. Sides of the quadrangular configuration are thus joined at corners defined by interaction of each of the plurality of spars of the demountable frame with respective pockets and sleeves of the canopy.

Abstract: Example implementations may relate to using an unmanned aerial vehicle (UAV) dedicated to deployment of operational infrastructure, with such deployment enabling charging of a battery of a UAV from a group of UAVs. More specifically, the group of UAVs may include at least (i) a first UAV of a first type configured to deploy operational infrastructure and (ii) a second UAV of a second type configured to carry out a task other than deployment of operational infrastructure. With this arrangement, a control system may determine an operational location at which to deploy operational infrastructure, and may cause the first UAV to deploy operational infrastructure at the operational location. Then, the control system may cause the second UAV to charge a battery of the second UAV using the operational infrastructure deployed by the first UAV at the operational location.

Abstract: Example implementations may relate to self-deployment of operational infrastructure by an unmanned aerial vehicle (UAV). Specifically, a control system may determine operational location(s) from which a group of UAVs is to provide aerial transport services in a geographic area. For at least a first of the operational location(s), the system may cause a first UAV from the group to perform an infrastructure deployment task that includes (i) a flight from a source location to the first operational location and (ii) installation of operational infrastructure at the first operational location by the first UAV. In turn, this may enable the first UAV to operate from the first operational location, as the first UAV can charge a battery of the first UAV using the operational infrastructure installed at the first operational location and/or can carry out item transport task(s) at location(s) that are in the vicinity of the first operational location.

Abstract: Various measures (for example methods, UAVs, controllers and computer programs) are provided in relation to controlling a UAV. The UAV is caused to provide energy to and receive energy from a given vehicle. The received energy is used to provide power to at least one component of the UAV.

Abstract: A vertical take-off and landing (“VTOL”) unmanned aerial vehicle (“UAV”) system and a method of controlling the same, wherein such method controls the stability and maneuverability of the VTOL UAV by manipulating the speeds of the propellers at each rotor. The VTOL UAV includes a body with three extending arms, wherein each of such arms is aligned and fixed at a certain angle from a central axis passing through the body. Each extending arm is equipped with a rotor with propellers. The rotors are sufficient to control the yaw of the UAV, and there is no need for coaxial rotors or an extra servo-motor in order to control the yaw of the UAV, thus reducing the cost and the weight of the UAV.

Abstract: A lightweight, pocket-sized unmanned aerial vehicle (UAV) that can be held in an outstretched hand by a user for take-off and landing of the UAV. The UAV comprises a semi-toroidal or a substantially toroidal hollow body that defines a duct. The UAV further comprises a motor for rotating a fan that directs air into and out of the duct enabling the UAV to take flight. The UAV comprises a flight-control system that comprises at least two flight control surfaces that can alter the directed air as it flows through the duct for controlling the roll and pitch and optionally the yaw of the UAV during flight. The flight control system may be controlled by a microprocessor controller. The UAV further comprises a payload, with at least a wireless transmitter and receiver unit.

Abstract: A payload retrieval system including a UAV having a payload receptacle positioned within the UAV, a payload coupling apparatus positioned within the payload receptacle, a tether having a first end secured within the UAV and a second end attached to the payload coupling apparatus, and a payload guiding member positioned on an underside of the UAV for guiding at least part of a payload into the payload receptacle during retrieval of a payload.

Abstract: A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

Abstract: A storage and transportation container for a radome of an aircraft is disclosed having a top wall, and bottom wall that are planar and parallel to one another, and a peripheral wall, wherein the top, bottom, and peripheral walls form an enclosure for supporting the radome within the container. The top wall has a closed curved outline and a surface of a dimension greater than that of the bottom wall having an outline which forms a parallelogram thus making it possible to receive the radome with its curved nose pointing downwards, and wherein the geometry of the container is matched to the form of the radome and of the hold.

Abstract: A pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

Abstract: Described herein are a system for providing oxygen to oxygen masks in an aircraft, and an associated method for regulating the oxygen flow in an efficient manner. The system has an oxygen tank, oxygen masks, first and second oxygen lines, and an electrically controllable valve. The valve is coupled to the oxygen tank and the two oxygen lines. The oxygen masks are coupled to the oxygen lines downstream of the valve to accommodate the transfer of oxygen from the oxygen tank via the valve. In a working state when an electrical signal is applied the valve produces a connection between the oxygen tank and the first oxygen line when required, and permanently prevents a connection between the oxygen tank and the second oxygen line. When in a rest state, the valve produces a permanent connection between the oxygen tank and the second oxygen line.

Abstract: The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure air

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

Abstract: An unmanned aerial vehicles (UAV) comprises an airframe, a battery mounted at the airframe, and a magnetic sensor mounted at the airframe. The battery comprises one or more multi-tab wound cells, the one or more the multi-tab wound cells comprise one or more electrode sheets and a plurality of tabs electrically connected to the one or more electrode sheets. An electrode sheet of the one or more electrode sheets is provided with one or more of the plurality of tabs. The magnetic sensor is spaced apart from the battery.

Abstract: A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

Abstract: An acoustic insert comprises a sleeve and a number of wave-shaped passageways within the sleeve. A contour of the number of wave-shaped passageways is selected to provide a desired level of attenuation for a frequency of sound waves entering the sleeve.

Abstract: Passive reduction of internal jet engine component temperature in supersonic and hypersonic vehicles results from use of nanocomposite optical ceramic materials between the heat-generating portions of each jet engine and the ambient environment, allowing heat dissipation from the jet engine components directly to the ambient environment. A propulsion-airframe integrated scramjet aircraft includes a jet engine and an airframe supporting the jet engine, with at least a portion of the airframe between a heat-generating portion of the jet engine and an ambient environment comprising a nanocomposite optical ceramic material in the form of a panel or a grid of windows each supported within a frame. The nanocomposite optical ceramic material portion of the airframe disposed between the heat-generating portion of the jet engine and the ambient environment is infrared-transparent, and may transmit at least 75% of heat energy from the heat-generating portion of the jet engine to the ambient environment.

Abstract: An airplane comprises a fuselage, two wings, engines, a rear tail unit comprising a horizontal tail provided with two tail ends, a first and a second set of fuel tanks, and a fuel transfer system configured to be able to transfer, at least in flight, fuel from one to the other of the first and second sets of fuel tanks, the tail ends being, in addition, mounted so as to be able to be pivoted, at least in flight, relative to the horizontal tail, the airplane thus having a configuration changeable in flight.

Abstract: A fuel tank inerting system is disclosed. The system includes a fuel tank and a catalytic reactor. The catalytic reactor is arranged to receive a first reactant from a first reactant source and to receive a second reactant from a second reactant source, and to react the first and second reactants to generate an inert gas. The system also includes an inert gas flow path from the catalytic reactor to the fuel tank. The catalytic reactor includes first, second, and third flow paths. The first flow path includes receives a first reactant and includes a reactive flow path including a catalyst. The second flow path receives a second reactant source and is in operative fluid communication with the first flow path through a first barrier between the first and second flow paths that is permeable to the second reactant. The third flow path receives a fluid coolant.

Abstract: A fuel tank inerting system is disclosed. The system includes a fuel tank and a catalytic reactor with an inlet, an outlet, a reactive flow path between the inlet and the outlet, and a catalyst on the reactive flow path. The catalytic reactor is arranged to receive fuel from a fuel flow path in operative communication with the fuel tank and oxygen from an oxygen source, and to catalytically react a mixture of the fuel and oxygen along the reactive flow path to generate an inert gas. An inert gas flow path provides inert gas from the catalytic reactor to the fuel tank. An adsorbent is disposed along the fuel flow path or along the reactive flow path.

Abstract: A fuel tank inerting system is disclosed. In addition to a fuel tank, the system includes a catalytic reactor with an inlet, an outlet, a reactive flow path between the inlet and the outlet, and a catalyst on the reactive flow path. The catalytic reactor is arranged to receive fuel from the fuel tank and air from an air source, and to react the fuel and air along the reactive flow path to generate an inert gas. The system also includes an inert gas flow path from the catalytic reactor to the fuel tank. The system also includes (a) an air distributor in the catalytic reactor arranged to distribute air along the reactive flow path, or (b) non-uniform catalyst loading or non-uniform catalyst composition along the reactive flow path, or both (a) and (b).

Abstract: A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.