A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.

A premium class passenger suite that includes a main seat positioned in the suite together with separate bed. The bed has a flexible mattress of predetermined dimensions and is movable between a stowed position to one side of the main seat and a deployed position above and separate from the main seat. A drive apparatus is provided for driving the bed between the stowed and deployed positions. The main seat is configured to be movable between a seating position when the bed is stowed, and a stowed position with a lowered seat back when the bed is deployed for use.

A seat cushion, in particular for an aircraft seat, the seat cushion comprising a seat part having a receiving surface adapted to receive a person and a reinforcing part supporting the seat part, wherein at least the reinforcing part contains expanded polypropylene (EPP), preferably comprising fire retardant properties. The invention further relates to a method for manufacturing such a seat cushion, a seat comprising such a seat cushion and a vehicle comprising such a seat.

An operating unit (1) for installation in an aircraft cabin comprises an operating unit front side (10) and an operating unit rear side (20), at least one operating element (12, 14) attached in the region of the operating unit front side (10) and accessible to a user, and a holding device (40) for attaching the operating unit (1) to a monument (30) accommodating the operating unit (1) in its state mounted in the aircraft cabin. The holding device (40) is designed to attach the operating unit (1) in its state mounted in the aircraft cabin to the monument (30), in a first position or in a second position, as desired, the operating element (12, 14) in the second position of the operating unit (1) being situated in a spatial position which is lowered with respect to the spatial position of the operating element (12, 14) in the first position of the operating unit (1) and/or is displaced in a direction parallel to an imaginary straight line connecting the operating unit rear side (20) to the operating unit front side (10).

A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold.

A generator includes a permanent magnet generator, an exciter and a main generator mounted for rotation on a shaft. The main generator is configured to produce a voltage output. A generator control unit includes a circuit configured to provide current from the permanent magnet generator to the exciter. A switch is provided in the circuit and is configured to change between open and closed conditions. The switch is configured to flow current in the circuit in the closed condition and interrupt current flow in the open condition. An overvoltage limit controller is programmed to determine an amount of overvoltage of the output voltage exceeding a desired voltage. Either a fixed reference threshold is used or a reference threshold voltage is calculated based upon the duration in over voltage condition, and the switch is modulated between the open and closed conditions according to error between the actual output voltage and the reference threshold voltage to limit the output voltage to the desired reference threshold voltage.

A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Baggage compartment 1 for an aircraft, wherein the baggage compartment 1 comprises a housing 2 and a baggage holder 3, wherein the baggage holder 3 is swivel-mounted about a swivel axis A in the housing 2, wherein, the swivel axis A intersects, in its longitudinal extent, a holder side wall 32 of the baggage holder 3 and/or a housing side wall 21 of the housing 2, wherein the baggage holder 3 can be moved from a closed position G into an open position Ö with a first swivel movement S1 and the baggage compartment 1 is opened and wherein the baggage holder 3 can be moved from the open position Ö into the closed position G with a second swivel movement S2 and the baggage compartment 1 is closed, wherein the baggage compartment 1 comprises a drive device 6 having at least one drive motor 9, wherein the drive device 6 is designed to drive the baggage holder 3 during the first and/or second swivel movement S1; S2 and to open or close the baggage compartment 1, wherein the drive device 6 is connected to the holder side wall 32 on one side and to the housing side wall 21 on the other side.

A spacecraft carrier is disclosed. The carrier has a large internal volume for housing at least one spacecraft. The carrier can be used as a repair and maintenance facility in space for spacecraft. Manned and unmanned devices can be stored, repaired and resupplied. The carrier can also transport a number of spacecraft to other locations allowing for an efficient coordinated movement of many spacecraft.

A method of creating at least one flight plan of an aircraft includes entering a creation objective which illustrates a type and general characteristics of the flight plan to be created, automatically generating a flight plan outline, automatically generating a targeted request for information relating to missing parameters, entering the requested information relating to the missing parameters, and supplementing automatically the flight plan outline and automatically deleting any discontinuities to create, in a definitive manner, the flight plan.

A method of controlling a group (2) of engines developing a necessary power (Wnec) for driving a rotor (3), said group (2) of engines having at least one electrical member (4), electrical energy storage means (5), and a first number n of engines (6) that is greater than or equal to two. A processor unit (10) executes instructions for evaluating a main condition as to whether the group of engines can develop the necessary power while resting one engine, and if so for resting one engine and accelerating a second number engines not at rest, and for causing the electrical member to operate in motor mode, if necessary, the electrical member operating temporarily in electricity generator mode when the storage means are discharged.

An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

A space efficient lavatory module for commercial aircraft includes an aft facing concave wall recess that provides a greater distance from an upper, forward facing portion of a cabin structure, such as an aircraft passenger seat to avoid having a passenger's head impact the aft facing lavatory or enclosure wall in a sudden aircraft deceleration. The aft facing concave wall recess also provides space for mounting of a protective cushion, in order to reduce a passenger's risk of head trauma in a sudden deceleration, as well as other items, such as a video monitor, a bassinet or infant bed, without inhibiting passenger movement.

In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

A system and method for mitigating an aircraft incident is provided. The invention includes an aircraft panic component coupled to a terminal component. The aircraft panic component facilitates identification of a panic situation and communicates information associated with the panic situation to the terminal component. The aircraft panic component is further operative to at least partially disable a navigation system and/or operational system of an aircraft. The aircraft can then be sent to a safe zone, navigated remotely and/or a course of action for the aircraft can be determined. A safe zone component is adapted to facilitate identification of a course of action for the aircraft based at least in part upon aircraft positional information, aircraft condition information and/or aircraft resource(s). Further, aircraft navigational information and/or aircraft operational information can be sent via an aircraft communication component to a remote system having a remote communication component and a remote analyzing component facilitating transfer of information related to navigational and/or operational system(s) of the aircraft.

A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer.

The present invention relates to landing gear (5) having at least one undercarriage (10) comprising a landing gear leg (11) carrying at least one wheel (12). The undercarriage (10) includes a retraction actuator (20) having an electric motor (23), blocking means (30) for blocking the actuator in the retraction position and for enabling the retraction actuator to be positioned in the “landing gear extended” position by gravity, first monitoring means (35) for monitoring the operation of the retraction actuator (20), first control means (65) for controlling the refraction actuator (20), and second control means (75) for controlling the blocking means (30).

A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

A spacer and gasket assembly is shown for receipt between a static structure having an outer and inner surface and fastener holes therethrough and a removable structure having a base with fastener holes and an upper surface and a lower surface. The static structure and removable structure are engaged through a multiplicity of fasteners having a shaft diameter. The fasteners are adapted to apply a compression on the gasket between the static structure and the removable structure. The static structure and the removable structure have opposed, typically flat, facing walls. The spacer and gasket assembly comprising a substantially non-compressible spacer adapted for receipt between the static structure and the removable structure having a spacer thickness. A gasket has a deformable, flowable, elastomeric body and a skeleton having a skeleton thickness, the skeleton substantially integral with the body. The gasket has an uncompressed gasket thickness. The spacer and the gasket are adapted to be placed substantially between the facing walls of the static structure and the removable structure and the removable structure will compress and deform the gasket when the fasteners are torqued down.

An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.

According to one embodiment of this disclosure an integrated fuel cell and environmental control system includes a turbo-compressor. The turbo-compressor includes a rotatable shaft, a compressor rotatable with the shaft to generate a flow of compressed air, a motor connected to the shaft, and a turbine connected to the shaft. The system further includes a fuel cell connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell. The fuel cell is connected to the turbine by a fuel cell exhaust line that supplies a flow of fuel cell exhaust to the turbine and causes the turbine to rotate. The system further includes an environmental control system connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system.

A mounted assembly of a wheel and a tire. The tire inflation pressure is greater than 9 bar, and a relative deflection of the tire greater than 30%. The rim comprises a drop-center functionality and is of monobloc type. A carcass reinforcement includes a circumferential alignment of carcass reinforcement elements anchored in the beads by a stack of circumferentially oriented reinforcement elements, and by an anchoring rubber mix having an elasticity modulus of less than 30 MPa at 10% deformation.

A method for producing a metal part, the part including, in particular, a first set of elements having a small thickness, and a second set of elements having a large thickness, the method including: forming a peripheral portion of the elements of the second set of elements by selectively melting a powder by scanning the surface of the powder layer with a laser beam or with an electron beam; using the peripheral portion of the elements of the second set of elements as a mould by carrying out an operation of filling an inner area defined by the peripheral portion with liquid metal; cooling the metal part to solidify the inner area defined by the peripheral portion and filled with metal.

A fuselage panel made of composite material having a skin with an opening, at least part of the contour of which is reinforced by an integrated reinforcement made of composite material. The fuselage panel includes at least one liner made of composite material which is attached to and superposed on the reinforced skin portion and participates at least partially in defining the contour of the opening, the panel additionally including consolidating members, each passing at least partially through the liner and at least partially through the reinforced skin portion.

The invention relates to a method for guiding an aircraft along a reference path, said method comprising: a) when the altitude of the aircraft is greater than a threshold, estimating (E1) a relative location of the aircraft in relation to a taxiing starting point using a map of the platform and reference points on the ground, b) when the altitude of the aircraft is less than said threshold and before the aircraft is located at the taxiing starting point, estimating (E2) a relative location of the aircraft in relation to the taxiing starting point using data relating to the absolute location of the aircraft and the last relative location estimated at step a), c) when the aircraft is located at the taxiing starting point, guiding (E3) the aircraft on the basis of a location of the aircraft relative to the reference path as estimated using data relating to a set of indicators on the ground.

A portable bracket is removably attached to a structure, such as a tree, for the purpose of relieving the strain on a hunter who is holding and aiming their firearm. A bracket comprising a back plate and a horizontal plate is secured to a tree using a strap and binder arrangement. The firearm support is portable and lightweight and maybe useful for other purposes within a campsite, such as holding a lantern and a like.

A watercraft includes a watercraft body, a watercraft propulsion device, a water protective case, a communication device, and a display device. The watercraft propulsion device propels the watercraft body. The water protective case is arranged on the watercraft body. The communication device communicates with a mobile terminal arranged inside the water protective case. The display device displays content of the mobile terminal based on data received from the mobile terminal through the communication device.

Planing hull extensions for watercraft are disclosed which may be mounted along the sides of the hull of a watercraft such as a boat or yacht. Typically, the hull extensions may be disposed along the side chines of the hull such that they extend the effective beam of the hull. The hull extensions may aid stabilizing the watercraft and/or inhibit wetting of the sides of the hull as well. In some cases, the hull extensions may be hydraulically operated between a closed position against the hull (or into a pocket along the side of the hull) and a fully open position substantially extending the width of the hull bottom. The position of the hull extensions may be automatically varied based upon throttle position, e.g. fully open at low throttle to fully closed against the hull at full throttle. Different hull extension position profiles may be used according to loading and water conditions.

A craft includes a rigid hull (1) that consists of a V-shaped bottom (5) and a bridge (4) on which a load can rest. The hull includes plating consisting of compartmentalized pneumatic floats (2), the rear compartments (32) of which are combined with an inflation and deflation system so as to vary the buoyancy of the craft. The craft also includes a submergible hull (1), the central cavity (9) of which is formed between the bottom (5) and the bridge (4) and is open at the rear so as to be automatically filled or emptied, the central cavity (9) containing at least one bag (10) that is combined with an inflation and deflation system enabling the buoyancy to be varied and consequently the level of immersion of the stern (7) to be changed as needed.

The general field of the invention is that of the graphical representation of a synthetic three dimensional view of the exterior landscape in an onboard visualisation system for aircraft, said graphical representation being displayed on a visualisation screen comprising the piloting and navigation information of said aircraft superposed onto said three-dimensional synthetic representation of the exterior landscape, said synthetic representation being computed up to a first determined distance, characterised in that said three-dimensional synthetic representation is tilted at a tilt angle about an axiom positioned at the level of the terrain in a substantially horizontal plane, and substantially perpendicularly to an axis between the flight direction and the heading of the aircraft, said axis moving with the aircraft.

This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

An electromechanical actuator for a movable flight control surface of an aircraft, the actuator comprising an electric motor having an outlet shaft with first and second directions of rotation, a movement transmission arranged to connect the outlet shaft of the motor to the movable flight control surface, and a control unit for controlling the motor. The transmission incorporates a pawl device arranged to oppose the transmission of movement in the first direction of rotation, and the control unit is connected to a pawl declutching member for declutching the pawl and enabling movement to be transmitted in the first direction of rotation.

Systems and methods for providing aircraft heading information are provided. In one embodiment, an attitude heading reference device comprises: at least one interface for receiving heading information from one or more IRUs; at least one set of gyroscopes and accelerometers; a memory device for storing data representing heading information received via the at least one interface; and a heading calculator coupled to the at least one interface, the at least one set of gyroscopes and accelerometers, and the memory device. The heading calculator generating a heading output signal based on heading information when reliable heading information is received over the at least one interface; the heading calculator generating the heading output signal based on data from the memory device regarding previously reliable heading information and an output of the at least one set of gyroscopes and accelerometers when reliable heading information is not received over the at least one interface.

This application relates to a baren 100 comprising a base 20 having a substantially flat surface 21 adapted for applying pressure to a work piece and a handle 10 removably connected to the base 20, wherein the handle 10 has an end that is adapted to receive a craft blade 60. the application also relates to a stamp 200 comprising a base 20' having a stamping surface 50 adapted for transferring a marking medium from the stamping surface 50 to a substrate and a handle 10' removably connected to the base 20', wherein the handle 10' has an end that is adapted to receive a craft blade 60.

The invention provides an arrangement and methods for thermally insulating aircraft, particularly but not exclusively for when the aircraft is operating in extremely hot or cold conditions, and describes an aircraft skin construction including a foam-stiffened CFC sandwich panel forming part of the aircraft outer skin mounted to an underlying load bearing aircraft structure, wherein the panel at the mounting to the structure includes two outer layers of CFC material with an inner layer of foam material sandwiched therebetween.

A method for controlling a pressure control mechanism in a turbofan engine having a precooler permitting heat exchange between ambient air and bleed air includes detecting at least one of an engine failure or a bleed system failure, detecting at least one of an ice condition or an activation of an anti-ice system, and actuating the pressure control mechanism, thereby altering the heat exchange between the ambient air and the bleed air.

An assistance device for an aircraft free-turbine turbine engine, the device including first electrical power supply for powering a winding of a starter rotary machine, referred to as a “first” winding, in order to provide first assistance in accelerating the gas generator of the engine. The device further includes a monitor for monitoring the first assistance, and a second power supply for electrically powering a second winding of the rotary machine to provide second assistance in accelerating the gas generator if the monitor observes that the first assistance is insufficient.

A multi-axis passenger-carrying aircraft comprises: an electrical system; a heat exchange system; a cabin; and an accommodating compartment arranged inside the cabin; wherein the electrical system is arranged inside the accommodating compartment, and wherein the heat exchange system comprises at least an air inlet communicated with the exterior of the cabin, an air outlet communicated with the accommodating compartment, and a cooler with an air inlet end communicated with the air inlet and an air outlet end communicated with the air outlet. In operation, air outside the aircraft may enter the heat exchange system via the air inlet and the cooler via the air inlet end to be cooled by the cooler. The cooled air may be discharged via the air outlet end and then enter the accommodating compartment via the air outlet, providing cool air to the accommodating compartment and dissipating heat from the electrical system.

Multi-axis passenger-carrying aircraft is provided, including: a heat exchange system; a cabin; and a passenger accommodating compartment arranged inside the cabin; wherein the electrical system is arranged inside the passenger accommodating compartment, and wherein the heat exchange system at least includes an air inlet in communication with the exterior of the cabin, an air outlet in communication with the passenger accommodating compartment, and a cooling and heating device with an air inlet end communicated with the air inlet and an air outlet end communicated with the air outlet. In operation, air outside the aircraft may enter the heat exchange system via the air inlet and the cooling and heating device via the air inlet end to be cooled or heated by the cooling and heating device. The air after heat exchange may be discharged via the air outlet end and enter the passenger accommodating compartment via the air outlet.

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AN EXQUISITE £2.5 million sanctuary originally built for the man who was the solicitor for the White Star Line during the Titanic enquiry, this 6,000 sq ft property is the only Test Valley home designed by the revered Arts and Crafts architect MH Baillie Scott.

Plugin Boutique has launched a sale on the Armory drum instrument by Stagecraft, offering 80% off for a limited time. The plugin comes with ADSR, cue points, independent tempo and pitch-shifting for any sample, effects chaining, and a massive catalogue of drum sounds. As with all of Stagecraft’s plugins, the displays they add are in-depth […]

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“We have bagged a multi-million dollar order from the Ministry of Defence to make rucksacks for the Indian army. It is an unchartered territory but creating an ideal rucksack for an Indian jawaan who spends maximum time outdoors in challenging terrain will be good learning. The order will be executed next year,” said Siddharth Sood, cofounder of Wildcraft India.

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THE CREATORS: Through the elegant, artistic lights she designs, creates and installs, Conway transforms places, perceptions and experiences.