A life vest container, a method for assembling a life vest container and a method for removing a life vest from a life vest container are disclosed. In an embodiment a leg rest includes linkages of a deployment and stowage mechanism, the linkages of the deployment and stowage mechanism being connectable to a seat, a mounting fixture connected to the linkages and a container secured to the mounting fixture, the container being configured to store a life vest.
In an embodiment a leg rest includes a mounting fixture, an extension frame and a deployment and stowage mechanism configured to deploy the leg rest from or stow the leg rest to a seat, wherein the extension frame is movably connected to the mounting fixture so that the extension frame moves relative to the mounting fixture when the deployment and stowage mechanism moves the leg rest relative to the seat.
A system for storage includes a drawer configured to open with a push, a drawer base, and a seat. A drawer face of the drawer is free of a handle. The drawer opens in a first direction along two or more slides. The drawer base is under the drawer, the drawer being coupled to the drawer base. The seat is over the drawer. The seat faces perpendicular to the first direction.
A heated seat for an aircraft includes a heating element disposed on a cushioning material and overlayed by an upholstery. The heating element includes a flexible base and a plurality of thin and flexible heating coils that conform to the seat shape such that no cushioning material is applied between the heating element and the upholstery. By providing direct contact between the heating element and the upholstery, smaller heating elements requiring less electrical power may be used to sufficiently heat the seat compared with traditional heating elements.
A system and method for a central control arm with tensioning for a lateral tracking and swivel system in a seat are provided. The control system includes a central control arm body, where the central control arm body has one or more attachment points and a cable interface feature, one or more paddle arms, and one or more adjustment mechanisms attached to the central control arm body, where each adjustment mechanism of the one or more adjustment mechanisms is aligned longitudinally along the central control arm body with a respective attachment point of the one or more attachment points, where each adjustment mechanism of the one or more adjustment mechanisms has a set screw that impinges on a face of a paddle arm of the one or more paddle arms.
An aircraft seat includes a base frame; a seat frame rotatably connected to a top side of the base frame, wherein the seat frame is configured to rotate about a vertical axis; a slot plate connected to the top side of the base frame, wherein the slot plate has a slot in a top surface of the slot plate; and a pin mount connected to a bottom side of the seat frame, wherein the pin mount has a pin that protrudes downward, wherein the pin is configured to protrude into the slot when the seat frame is rotated into a first orientation relative to the base frame.
A seat release system and device, the system including an interface assembly that provides actuation signaling, an actuation device that communicatively provides mechanical motion in response to the actuation signaling, a cable connected to the actuation device, and a recline release cylinder having a gas release button and a release lever at a first end, and having a cylinder piston arm in the recline release cylinder at a second end. The release lever is attached to a second end of the cable where the cable moves the release lever in response to the mechanical motion of the actuation device. The gas release button vents the recline release cylinder to atmosphere in response to being depressed as a result of the cable moving the release lever. The cylinder piston arm may move in the recline release cylinder in response to the gas release button being depressed.
An embodiment seat control system includes a control board having a processing unit, wherein the processing unit has one or more processors and one or more memories, and a mainboard. The processing unit is communicatively attached to the mainboard and mainboard has a plurality of receptacles and mainboard includes one or more communication buses between at least one of the plurality of receptacles and the processing unit. The system further has one or more system modules, where each module of the one or more system modules is configured to be connected to a respective receptacle of the plurality of receptacles, where each module of the one or more system modules implements a functional capability of a seat, and where the one or more system modules are nondestructively removeable from the mainboard.
A wire twisting device may include a driven rotating mechanism having a groove configured to receive two wires, an electric motor associated with an encoder, wherein the encoder is configured to generate an electrical signal corresponding to changes in rotation of the electric motor, a drive gear mechanically coupled with the electric motor for rotating the driven rotating mechanism, a current sensor on a printed circuit board configured to detect an electrical current to the electric motor and generate a voltage that corresponds to the amount of electrical current, and a control unit configured to perform steps comprising: receiving the electrical signal generated by the encoder, receiving the voltage generated by the current sensor, determining an amount of torque applied to the two wires; and when the amount of torque exceeds a predetermined limit, communicating a control signal to reduce the electrical current provided to the electric motor.
B21F 7/00 - Torsion des fils métalliquesTorsion de plusieurs fils ensemble
B21F 15/04 - Assemblage de fils métalliques entre eux ou à d'autres matériaux ou objets métalliquesAssemblage d'éléments au moyen de fils métalliques de fils entre eux sans autres éléments ou matériaux de connexion, p. ex. par torsion
According to an embodiment, a duct for fluid transport includes a first duct segment and a second duct segment, each segment being formed using an additive manufacturing process. Each segment includes a body region and an edge region, with the second segment being configured to couple with the first segment along the edge region. The duct also includes at least one projection extending from the edge region of the first segment and at least one recess disposed along the edge region of the second segment, with the recess being substantially similar in shape to the projection. Additionally, at least one of the first duct segment and the second duct segment includes a lip extending along the length of the edge region.
An electric aircraft includes a forward wing and an aft wing both located on a top side of a fuselage and both having an upward dihedral angle. The forward wing has a straight or slightly forward-swept leading edge. The aft wing has a swept leading edge. A plurality of propeller engines are located on a leading-edge side of the forward wing. A single propeller engine may be located on a top side of an aft end of the fuselage; alternatively, a plurality of propeller engines are located on the aft wing on either its leading or trailing edge. The propeller engines are each powered by an electric motor. An unobstructed cargo door is located on a side of the fuselage, aft of the forward wing.
A system for establishing an auxiliary electrical connection for an igniter configured to puncture a fire bottle. The system having an adapter configured to conceal an electrical connection of the igniter and electrically couple the concealed electrical connection to the auxiliary connection. The auxiliary connection preventing an improper connection being made to the igniter by having a different connection size than the electrical connections on the igniter.
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
A62C 37/36 - Commande des installations de lutte contre l'incendie le signal de déclenchement étant émis par un détecteur distinct de la tuyère
A battery system includes a first battery cell; a second battery cell positioned adjacent to the first battery cell; and a fusible link connecting the first battery cell to the second battery cell. The fusible link having a first tab connected to and extending from the first battery cell; a second tab connected to and extending from the second battery cell; and a connection connecting the first tab to the second tab; the connection is to release the first tab from the second tab upon being heated to a threshold temperature; and releasing the first tab from the second tab protects the first battery cell from thermal runaway conditions of the second cell.
H01M 50/516 - Procédés pour interconnecter les batteries ou cellules adjacentes par soudage, brasage ou brasage tendre
H01M 10/0525 - Batteries du type "rocking chair" ou "fauteuil à bascule", p. ex. batteries à insertion ou intercalation de lithium dans les deux électrodesBatteries à l'ion lithium
H01M 50/534 - Connexions d’électrodes dans un boîtier de batterie caractérisées par le matériau des conducteurs ou des languettes
H01M 50/581 - Dispositifs ou dispositions pour l’interruption du courant en réponse à la température
An aircraft weight and balance system includes a user interface that displays an interior layout of an aircraft with seat icons and cargo icons corresponding to seats and cargo zones onboard the aircraft. The seat and cargo icons are moveable to different locations within the interior layout, and an updated weight and center-of-gravity of the aircraft is automatically determined based on the different locations of the seat and cargo icons. An aircraft weight and balance method includes displaying an interior layout of an aircraft on a user interface including seat icons corresponding to seats onboard the aircraft, moving one or more of the seat icons to a different location within the interior layout based on a user input, determining an updated weight and center-of-gravity of the aircraft based on a current location of the seat icons, and displaying the updated weight and center-of-gravity of the aircraft on the user interface.
G01G 23/37 - Dispositifs indicateurs, p. ex. pour indication à distanceDispositifs enregistreursÉchelles, p. ex. graduées indiquant le poids par des moyens électriques, p. ex. par utilisation de cellules photo-électriques impliquant un comptage numérique
G01G 19/07 - Appareils ou méthodes de pesée adaptés à des fins particulières non prévues dans les groupes pour peser des objets à roues ou roulants, p. ex. des véhicules pour peser des avions
G01M 1/12 - Équilibrage statiqueDétermination de la position du centre de gravité
A window roller shade and dimming pane assembly includes a rigid frame having a first side member on a first side and a second side member on a second side opposite the first side. An outer pane and an inner pane are disposed within the rigid frame with a gap between the outer pane and the inner pane. A roller shade includes a motor for rolling and unrolling the roller shade. A first constant force spring and a second constant force spring are each configured to pull the roller shade downwardly through the gap while the motor is unrolling the roller shade. A dimming film is disposed on the inner pane for dimming light through the inner pane. A window interface is operatively coupled to the inner pane for receiving touch input for controlling the dimming film and the roller shade.
A system and method for defeating a door lock. More specifically, a door having an outside door handle with a key-lock, and having an interior door handle of the type that includes both a paddle along with the handle runs the risk of being left in locked mode in the event of a mechanical malfunction. This problem has been overcome by mechanically linking the paddle on the interior handle to unlatch the key-lock.
E05B 77/30 - Fonctions relatives à l’actionnement des serrures depuis l'habitacle du véhicule permettant l’ouverture par une poignée de porte intérieure, même si la porte est verrouillée
E05B 83/36 - Serrures pour portières passagers ou similaire
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
An aircraft door system and related closure method. The system involves the use of a ball transfer device as an initial contact made in the closing of an aircraft door. The closing door next encounters guiding and fitting arrangements are also employed to laterally align the lower portion of the aircraft door with the corresponding portion of the frame upon the closing. Finally, the closing door then encounters load path ties which are employed about the door. The arrangement above allows the door refit the door within what is a deformed doorframe due to weight and structural considerations.
A door sill protector includes a base rotatably mounted to a door sill via a hinge. The hinge allows the base to be rotated between a stowed position and a deployed position. A plurality of support feet are disposed on an underside of the base. Each of the support feet is pivotable for pivoting between an extended orientation and a retracted orientation. A linkage bar is mechanically coupled to the support feet such that the support feet collectively pivot in unison between the extended orientation and the retracted orientation.
A doorway side guide system includes a base mechanically coupled with a bottom portion of a doorway. A mounting member is rotatably coupled to the base via a hinge for rotating between a deployed position and a stowed position. A contact member is mechanically coupled with the mounting member via a pivot such that the contact member is configured to rotate about the pivot. The contact member extends outside of the doorway in the deployed position for guiding cargo through the doorway and for protecting a doorframe of the doorway.
A system and method for unlatching an aircraft door is disclosed. The system includes a latch pin design which enables retraction of the pin in the event the ordinary unlatching mechanical systems fail. The system includes the use of a rod that is reversely threaded on each side. Rotation of the rod either extends or retracts the pin.
A handle assembly for an escape hatch. A handle assembly for an escape hatch comprises an interior handle and an exterior handle. The interior handle has an interior cam associated therewith and the exterior handle has an exterior cam associated therewith. The interior cam and the exterior cam each have a concave profile surface and a curved profile surface. A middle cam is sandwiched between the interior cam and the exterior cam and has a notched profile. The interior and exterior cams are associated with a tumbler having a flag. The middle cam is associated with an output rod operatively coupled to a second flag. Each of the interior handle and the exterior handle can be successively rotated in a first arc of rotation and a second arc of rotation with one hand. The first and second arcs of rotation are respectively associated with the flag and the second flag.
An escape hatch stay system for an aircraft and methods of using the escape hatch stay system. An escape hatch stay system includes a first stop arm, a second stop arm, and a gas strut. The first stop arm is rotatably coupled to the second stop arm, and the second stop arm is pivotably coupled to the gas strut. The first and second stop arms are lockable to preclude relative movement therebetween to lock the escape hatch in an open position. When the escape hatch is in the open position, the escape hatch may not be closed shut without manual intervention. When the escape hatch is in the open position, a load applicable to push the escape hatch open past the open position is damped by the gas strut.
E05C 17/32 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs par des moyens mécaniques par une barre mobile ou une pièce équivalente disposée entre le dormant et le battant consistant en plusieurs tringles pivotantes
E05F 1/10 - Appareils de fermeture ou d'ouverture pour battants, non prévus ailleurs dans la présente sous-classe actionnés par ressort pour battants pivotants
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
23.
Pneumo-Mechanical Landing Gear Deployment System and Method
A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.
A latch positioning mechanism for an aircraft door includes one or more locking members configured to be partially driven into a frame around the door via rotation of a pivot pin. A frame bumper extends outside of the door in a pre-catch position for contacting the frame. A catch bellcrank is operatively coupled to the frame bumper, and a biasing member biases rotation of the catch bellcrank to bias the frame bumper into the pre-catch position. The catch bellcrank is configured to contact a catch cam when the catch bellcrank is biased into the pre-catch position such that the catch cam prevents release of the one or more locking members for locking the door. Upon the frame bumper contacting the frame when the door is closed, the catch cam is released enabling the one or more locking members to be moved into a locked position.
E05B 83/36 - Serrures pour portières passagers ou similaire
E05B 77/22 - Fonctions relatives à l’actionnement des serrures depuis l'habitacle du véhicule
E05C 9/24 - Moyens de transmission des mouvements entre des barres, tringles ou câbles coulissant verticalement et horizontalement, p. ex. renvois d'angle
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
A tandem split divergent winglet for an aircraft includes a forward sail extending from an outboard end of a wing of the aircraft having a cant angle in a first direction, and an aft sail extending partially from the forward sail and partially from the outboard end of the wing. The aft sail has a cant angle in a second direction opposite the first direction. For aircraft having a low wing, the forward sail includes an upwards cant angle and the aft sail includes a downwards cant angle. For aircraft having a high wing, the forward sail includes a downwards cant angle, and the aft sail includes an upwards cant angle. Light emitted from an integrated light formed within the aft sail is blocked from reaching a cockpit window of the aircraft by the forward sail.
A flag mechanism for an aircraft door includes a first arm and a second arm each having a flag on a first end and a catch on a second end. A first cam is operatively coupled to a first latching member and a second cam is operatively coupled a second latching member. The first and second latching members are each configured for latching the aircraft door, which are locked when the first and second cams are rotated to a locked position. A first stud extends from a side of the first cam and a second stud extends from a side of the second cam. The first and second studs are each configured to be received by a respective catch of the first and second arms while the first and second cams are rotated, thereby moving each respective flag from a first position to a second position for simultaneous visual inspection.
An oil level measurement system for an aircraft engine includes a magnetic float disposed in the aircraft engine, a first sensor ladder configured for sensing a position of the magnetic float, and a second sensor ladder configured for sensing a position of the magnetic float. A controller is configured to determine an oil level of an engine based on an engine status signal, a first signal from the first sensor ladder, and a second signal from the second sensor ladder. An oil level sensing method for measuring an oil level within an aircraft engine when the aircraft engine is off includes comparing a first signal from a first sensor ladder with a second signal from a second sensor ladder, indicating a fault when the first signal is different from the second signal, and determining an oil level of an aircraft engine when the first signal matches the second signal.
G01F 23/72 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme par des flotteurs du type à flotteur libre en utilisant des moyens d'indication actionnés magnétiquement
H01H 36/02 - Interrupteurs actionnés par la variation du champ magnétique ou champ électrique, p. ex. par le changement de la position relative d'un aimant et d'un interrupteur, par écran actionnés par le mouvement d'un flotteur portant un aimant
F01M 11/12 - Dispositifs indicateursAutres dispositifs de sécurité concernant le niveau du lubrifiant
A fixture configured to secure a component in a vehicle includes a panel separating an internal cabin from an external compartment. The panel has a first side facing the internal cabin and a second side facing the external compartment. A hole is disposed within the panel. The component is configured for mounting to the panel via the hole. The component includes a flange configured for abutting the first side of the panel and a coupling feature configured to extend through the hole into the external compartment. A fastener is configured to removably couple with the coupling feature and abut the second side of the panel for fastening the component to the panel.
B64D 47/02 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
B60Q 3/54 - Dispositifs d’éclairage intégrés dans l’habillage intérieur, p. ex. dans les habillages de plafond
A method for automatically decoding aircraft Cockpit Voice Recorder (CVR) encoded data includes loading a definitions class and a decoder class into a memory via a driver class, loading configuration files into the memory via the definitions class, receiving from an aircraft CVR one or more hex files that include the CVR encoded data into the memory, generating via the decoder class and the configurations file one or more decoded objects based on the one or more hex files, respectively, and displaying the one or more decoded objects in a human readable format. A system to automatically decode aircraft CVR encoded data includes a user interface, a processor, and a memory having a computer program configured to generate one or more decoded objects based on one or more hex files of CVR encoded data, and to display the one or more decoded objects in a human readable format.
Disclosed is an electronics device holder made to be mountable on an aircraft control stick arrangement. The holder enables two dimensions of rotation. Rotation clockwise and counterclockwise is provided by a disk on which the holder is mounted. The disk edges are trapped underneath a containing plate. Friction enables the disk, and thus, the holder to be held in different circular positions. A friction hinge is used to establish and hold different pitch positions for the electronics device.
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objetsMoyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p. ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
F16M 11/10 - Moyens pour la fixation des appareilsMoyens permettant le réglage des appareils par rapport au banc permettant la rotation autour d'un axe horizontal
A compression-force spike reduction system for a strut includes a first chamber and a second chamber, an orifice plate disposed within the strut between the first chamber and the second chamber, a hydraulic fluid disposed within the first chamber and the second chamber, and a compressible portion disposed in the second chamber. The orifice plate includes at least one orifice configured for the hydraulic fluid to flow through. During compression or extension of the strut, hydraulic fluid is exchanged between the first chamber and the second chamber. The compressible portion contains a compressible medium configured to buffer spikes in compression force of the strut. A compression-force spike reduction method includes filling the second chamber partially with the incompressible hydraulic fluid, and filling a remaining portion of the second chamber with a compressible medium.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
A stowable entry handle includes a handle having a first end and a second end opposite the first end, a shaft mechanically coupled with the handle, a protrusion extending from an end of the shaft opposite the handle, and a mounting structure for mechanically coupling to a side wall adjacent a doorway. The shaft includes a cylindrical member that extends perpendicularly from the first end. The mounting structure includes a tube configured to receive the shaft. The tube includes a first slot at a first position within the tube and a second slot at a second position within the tube. The protrusion is configured to insert into the first slot for stowing the handle inside the doorway and the second slot for deploying the handle outside the doorway.
A stairway for aircraft is disclosed which includes first and second stair halves, one which nests in the other. The first half is hinged to the doorway and the second half is hinged to the first half. A mechanical resistance system uses different devices to allow for the airstair to be damped when switching between modes. A retracting arrangement is also disclosed.
An aircraft stair system is provided with flexible bumpers configured to prevent abrupt impact of the first structure against the second. Each of the bumpers has a flexible body, a base portion, and a lever arm extending out over the base to create a gap and an open mouth.
Opposing magnets are used to hold two hinged stairway portions together by including the magnets into opposing surfaces in an aircraft stairway arrangement. The relative position of one of the magnets relative to the other is used to establish a desired holding force.
A servo drive vernier control for aircraft having a push-pull mechanism configured for manual actuation by a user includes a push rod mechanically coupled with an input knob. The push rod is configured for manual actuation via the input knob. An electromechanical control system is operatively coupled with the push rod for providing automated operation of the push rod. The electromechanical system includes a motor operatively coupled to the push rod. The motor is configured to rotate the push rod for actuating the push-pull mechanism. A controller is communicatively coupled to the motor for enabling electronic control of the push-pull mechanism.
An overhead bin in an aircraft includes a liner disposed on an underside of a cabin ceiling and a receptacle that protrudes through an opening in the liner. A bin has a top side with at least one attachment point that includes: a stud mechanically coupled to the top side and a screw disposed within the stud. The stud includes a rounded flange configured to insert into the receptacle for removably securing the bin beneath the liner. An installation method for an overhead bin in an aircraft includes raising the overhead bin to engage the stud with the receptacle, sliding the overhead bin outboard for inserting the stud into the receptacle, and turning a screw within the stud for tightening the stud within the receptacle for securing the overhead bin beneath the ceiling.
A system for an automated cabin-divider door for an aircraft includes a door, a motor for moving the door to an open position, a limit switch configured to detect when the door is in a fully open position and to stop the motor, and electronics coupling the motor and the limit switch to an avionics system. The avionics system determines when the door is to be opened and provides a signal to the motor for moving the door to the fully open position. A method for automatically opening the cabin-divider door includes determining whether the aircraft is on the ground or in flight, determining whether the aircraft is taxiing, and determining whether the aircraft is in a final phase of approach. When the aircraft is taxiing or in the final phase of approach, the method includes sending a command signal to the motor for opening the cabin-divider door.
An oxygen pressure relief and ventilation system includes a flow fuse fluidly coupled downstream of a pressure regulator. The pressure regulator is operatively coupled to an oxygen tank, and the oxygen tank is located in an unpressurized compartment of an aircraft. A pressure relief valve is fluidly coupled downstream of the flow fuse. A ventilation pathway fluidly couples the unpressurized compartment with a pressurized compartment. The flow fuse and the pressure relief valve are configured to cooperatively mitigate downstream flow of pressurized oxygen if the pressure regulator fails. The ventilation pathway is configured to allow air from the pressurized compartment to pass through to the unpressurized compartment for diluting a concentrated oxygen in the unpressurized compartment.
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant pressurisé
G10K 11/16 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général
A door stop includes a scissor link member including a pair of links pivotably coupled together at a central pivot point. The scissor link member has a first end pivotally coupled to a door and a second end pivotally coupled to a floor. The pair of links are configured to abut against one another adjacent the central pivot point when the door is fully open to prevent pivoting at the central pivot point for holding the door open. The scissor link member is releasable such that the pair of links pivot about the central pivot point when the scissor link member is released, thereby enabling closing of the door. The pair of links fold into a nested arrangement when the door is fully closed. The pair of links are configured to deform under dynamic loads to protect the surrounding aircraft structure and indicate a need for inspection.
E05C 17/32 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs par des moyens mécaniques par une barre mobile ou une pièce équivalente disposée entre le dormant et le battant consistant en plusieurs tringles pivotantes
E05C 17/08 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs par des moyens mécaniques par une barre mobile ou une pièce équivalente disposée entre le dormant et le battant avec moyens particuliers de libération, p. ex. une libération automatique du fait que l'on continue à ouvrir
41.
Isolator Assembly with Adjustable Preload for Damping Air Load Forces
An isolator assembly is configured for damping vibrations of a sensor deployed outside of an aircraft. The isolator assembly includes a platform configured for mechanically supporting the sensor, a lift mechanism configured to raise and lower the platform for stowing the sensor inside the aircraft and deploying the sensor outside the aircraft, and a plate secured inside the aircraft beneath the platform. The plate includes a through-hole for the sensor to extend through. A pin extends below the platform and an isolator mount is disposed on a top side of the plate. The isolator mount includes a slot configured to receive the pin upon deploying the sensor outside the aircraft. The platform and the plate are configured to stabilize the sensor and the isolator assembly is configured to damp vibrations imparted on the sensor by the airstream during flight.
B64D 43/00 - Aménagements ou adaptations des instruments
F16F 15/04 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques
A storage retainer includes an open recessed area configured to store materials in an aircraft. The retainer includes an aft wall and a lower shelf for receiving materials thereon. The retainer includes one or more straps attach to a panel for securing objects, such as a flight manual, against the aft wall and the lower shelf. The straps attach to one or more anchors on the aft wall and one or more anchors on the lower shelf, therein biasing the panel towards the aft wall and the lower shelf to secure the materials in the open recessed area for easy access thereto.
A foldable vehicle seat includes a seat base having a seat support frame, a seat back extending from the seat base, and a foldable section connected to the seat back. The folded section has a folded and unfolded configuration, and comprises a hinge mechanism with a pivot point, a first support, a second support, and a top surface configured to store luggage thereon. The first support is connected to the hinge mechanism and is rotatable about the pivot point. Likewise, the second support is connected to the hinge mechanism and is rotatable about the pivot point. The first and second supports contain first and second magnets, respectively, which are configured to retain the foldable section in the folded configuration.
Disclosed is an automatic throttle arrangement utilizing a servo which receives commands from a controller on an aircraft and responsively rotates a mechanical device that is linked by a cable arrangement with the aircraft’s throttle lever enabling automated throttle control. The mechanical device can be fixed to the throttle lever assembly using rivets designed to fail in case the servo/cable arrangement jams. This leaves the lever able to continue manual function.
B64D 31/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A multi-chamber internally damped tuned vibration absorber includes a mass having internal chambers that house damping members for dissipating vibrational motion of the mass. Guide members pass through the internal chambers and guide movement of the mass. An attachment member attaches the guide members to a structure to attenuate vibrations of the structure.
F16F 15/08 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques avec ressorts en caoutchouc
A non-structural seat belt buckle cover is disclosed. The seat belt buckle cover may be used to protect seat belt buckles used on aircraft from damage. The seat belt buckle cover may comprise a top cover and a bottom cover that are coupled together to enclose a seat belt buckle. The seat belt buckle cover may comprise various openings to provide a user access to portions of the seat belt buckle.
A44B 11/25 - BouclesFermetures similaires pour attacher ensemble des courroies ou similaires, p. ex. pour ceintures des sécurité avec plusieurs pièces séparables
Disclosed is a system for connecting an edge of one panel to an edge of a second panel. Recesses are formed into the edges of each panel, and two distinct inserts are pressed into and held within the recesses. The inserts include holes for receiving epoxy, and epoxy conducting shafts and circuits are formed on the outside of the inserts to assist in the encapsulation of the insert within each panel edge.
F16B 11/00 - Assemblage d'éléments structuraux ou parties de machines par collage ou en les pressant l'un contre l'autre, p. ex. soudage sous pression à froid
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
A substructure in an aircraft cabin includes a drawer-insert accepting portion that defines multiple racks. Each rack may receive an exchangeable drawer insert. A module-accepting portion of the substructure defines an opening that includes a supporting surface, a back wall which extends upward and outward, and a lateral side wall. A module is provided for optionally installing in the module-accepting portion. The module has concealed areas upon installing that include: (i) a base adapted to rest on the supporting surface, (ii) a side wall adapted to abut the lateral side wall, and (iii) a rear wall adapted to abut the back wall. The module has exposed surfaces upon installing that are adapted to match an existing profile of the drawer-insert accepting portion. The module-accepting portion is configured for stowing cargo in a first mode and for receiving the module in a second mode. The module may include a locking assembly.
A mandrel mold tool for forming a mandrel includes a plurality of mandrel mold tool members that are configured for fastening together to form a mandrel mold tool having an internal compartment. The plurality of mandrel mold tool members each include an outer wall, an inner wall adjacent the outer wall, and an interior portion between the outer wall and the inner wall. The interior portion has a sparsely-infilled structure that is substantially permeable to fluids. The outer wall has a port for receiving a hardening fluid. The inner wall has a plurality of through-holes such that the hardening fluid, upon being introduced via the port, passes through the interior portion and the plurality of through-holes for hardening a sacrificial mold disposed in the internal compartment.
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B33Y 80/00 - Produits obtenus par fabrication additive
B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 33/44 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille
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