345results about "Aircraft floors" patented technology

A fastening device for releasable connection to a perforated rail of an aircraft and a method of assembly for such a fastening device. The fastening device comprises a housing having at least one locking head portion fixedly connected to the housing, at least one shear pin and an actuating pin. The locking head portion is insertable into a rail hole of the perforated rail and slidable along the longitudinal direction of the perforated rail to a locking position in which the locking head portion engages a slot portion of the perforated rail. The shear pin can be engaged with a rail hole of the perforated rail by axial displacement. The actuating pin is rotatably arranged relative to the housing and connected to the shear pin in such a way that a rotation of the actuating pin causes an axial displacement of the shear pin relative to the housing.

A floor system for a cabin of a vehicle is proposed, the floor system including a floor panel having a bottom layer, a top layer and a continuous stiffening structure having an alternating arrangement of elongated first depressions and elongated protrusions arranged between the bottom layer and the top layer, an elongated cover component, and at least one seat rail component. The cover component has an upper surface, a lower surface, and an elongated second depression reaching from the upper surface to the lower surface and having a shape that corresponds to the shape of the first depressions. The cover component is configured to be mounted inside a first depression that is accessible through an elongated cutout extending along a depression of the stiffening structure. The at least one seat rail component is attachable to the cover component to provide a seat rail along the floor panel.

A fixed-wing cargo aircraft having a fuselage wing cutout supported by box beam longerons is disclosed. The fuselage contains a continuous interior cargo bay, and includes a forward portion, an aft portion, and a cutout defined by a plurality of structural elements configured to transfer a wing load to the fuselage, the structural elements including opposite starboard and port longeron beams each spanning a longitudinal length of the cutout. The starboard and port longeron beams have an enclosed box beam construction, which can include a plurality of panel sections, at least one of the plurality of panel sections comprising a skin panel of the fuselage. The cutout can have forward and aft frame beams each having an enclosed box beam construction that form a structural perimeter of the cutout with the starboard and port longeron beams.

A structure system for installation into a fuselage structure in an interior of an aircraft is proposed, the system comprising at least one first carrier element, at least one second carrier element, at least one elongate frame element having a first end and a second end, at least one first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, at least one first coupling device mounted to the first end for coupling the first carrier element to the at least one frame element, and at least one second coupling device mounted to the second end for coupling the second carrier element to the at least one frame element, wherein the at least one frame element is adapted for holding at least one component to be installed in the interior, wherein the at least one first carrier element is designed for coupling with the at least one first coupling device, wherein the at least one second carrier element is designed for coupling with the at least one second coupling device, and wherein one of the at least one first coupling device and the at least one second coupling device is adapted to snap into the respective carrier element, to be moved relative to the respective end of the frame element and to be arrested in a desired relative position thereto.

A serrated fitting and method for installing fixed length roller tray segments spanning an aircraft fuselage integration zone. The serrated fitting includes a first surface for attachment to a fixed length roller tray segment. The serrated fitting also includes a serrated surface for engagement with a serrated plate attached to a floor beam of an aircraft. A fastener connects the serrated surface to the serrated plate and the floor beam through a pre-drilled hole in the floor beam. The pre-drilled hole is larger than the diameter of the fastener to accommodate accumulated tolerance between joined fuselage sections at a fuselage integration zone.

An air drop rack assembly is mounted within the cargo compartment of a cargo aircraft and has a forward part secured to the load deck and an aft part secured to the aircraft cargo ramp. The rack parts have rollers in conveyor assemblies mounted between C-channels which engage skidboards which support smaller aircraft such as gliders or cruise missiles. When the ramp is up two rack parts are tilted with respect to each other. At payload drop, ramp is deployed to bring the rack part conveyor assemblies into alignment. Although the aligned rack parts are spaced apart, when the cargo aircraft is tilted upwardly, the individual payloads on skidboards are discharged out the aircraft aft opening. Cruise missiles or bombs may be supported on a skidboard with a deformable surface, a forward ballast weight, and a spring, such that once launched the skidboard is pushed away from the payload.

A monument for installation in an aircraft passenger cabin comprises a housing extending from the floor upwardly toward the ceiling, the housing including a first configuration configured to receive a wheelchair in a first unfolded condition, and a second configuration configured to receive a stretcher in a second unfolded condition, a first interior space formed in the housing, a staircase disposed within the interior space; a second interior space formed in the housing, a first entrance into the first interior space through a door; a second entrance into the second interior space of the housing, and a securement assembly positionable on the floor, the securement assembly configured to secure one of the wheelchair or the stretcher in place within the interior space.

A fixation interface includes primary connection studs and secondary attachment interface components. Each connection stud includes a longitudinal axis, a mounting foot, and an interface head arranged along the longitudinal axis. The mounting foot form-fittingly fastens to a floor fastening point. On opposite lateral sides, the interface head includes protrusions extending traverse to the longitudinal axis. Each secondary attachment interface component mounts to an interface head by form-fittingly engaging the protrusions in a longitudinal direction. Each secondary attachment interface component is positionable to the interface head region in a positioning movement and is lockable in a locking movement. Each secondary attachment interface component includes first and second types of interface components. The first type are positionable and lockable in first positioning and first locking movements, and the second type are positionable and lockable in second positioning and second locking movements, the first and second locking movements being different.

A giant airliner structure comprises an airliner body and at least two layers of wings arranged on the two sides of the airliner body, a steering rudder is arranged between the upper and lower adjacent wings. The method has excellent environmental protection property and economical efficiency, and specifically comprises the steps that the core plate structure is adopted, and the labor cost needed in the production process is remarkably reduced; the structural design is simple, the maintenance difficulty is reduced, and the maintenance cost is reduced; the passenger-engine ratio is extremely low, and the manufacturing cost is greatly reduced; the weight ratio of the passenger plane is extremely low, and oil is greatly saved; the wings are short, the airport applicability is wide, and the opportunities of business are increased.

A method for monitoring an aircraft cargo bay using an aircraft interface device may comprise receiving image data of a cargo bay of an aircraft. The method may further comprise detecting movement in the cargo bay, directing a camera to activate in response to that movement, and processing the captured image data. The aircraft interface device may include pre-trained neural network based algorithms configured for event classification. The method may further comprise generating an alarm based on a theft event classification and transmitting the alarm to an aircraft.

The present invention belongs to the technical field of aircraft. Particularly, the present invention provides an aircraft fuselage section (1) with improved crashworthiness. The aircraft fuselage section (1) comprises a fuselage structure, a floor (3) connected to the fuselage structure, a cushioning element (4) arranged on the floor (3) and crash absorption means (5) arranged between the fuselage structure and the floor (3).

An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin is provided. The aircraft seat connector comprises a base portion for being introduced into the mounting rail and a seat connection portion. The seat connection portion extends from the base portion and is configured for being releasably coupled to an aircraft seat. The seat connection portion allows for coupling the aircraft seat to the seat connection portion in at least two different spatial orientations.

An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.

A connecting device including first and second off-center rings, the second ring being positioned in the first ring. The peripheral outer surface of the first ring is frustoconical and has a smaller cross section oriented in a first direction, and the inner surface of the first ring and the outer surface of the second ring, which surfaces interact with one another, have cross sections which increase between a first cross section and a second cross section that is offset in relation to the first cross section in an opposite direction to the first direction. This arrangement makes it possible to be able to prevent the rotation of the first and second rings once their angular positioning has been adjusted.

An aircraft (10) with a primary structure (11) is described. The primary structure (11) has a structural element (20) in the form of a wall and is defined by an extension in three spatial axes (17, 18, 19). The wall is characterized by a density gradient that varies along a longitudinal axis (17) of the primary structure (11) and is designed to displace a center of gravity (50) of the aircraft (10) along the longitudinal axis (17) of the primary structure (11) between a front end (15) and a rear end (16) of the aircraft (10) as a function of the varying density gradient.

A dynamically controlled cargo loading system for an aircraft includes electrical cargo conveying devices for conveying cargo items on a cargo loading deck; speed sensors, which are configured to capture current conveying speeds of the cargo conveying devices and / or the conveyed cargo items; electrical measuring devices, which are configured to capture current electrical parameters of the cargo conveying devices; and a control device which is configured to control the cargo conveying devices depending on the captured current conveying speeds and / or the recoded current electrical parameters such that at least one of the following variables is optimized: the electrical power consumption of the cargo conveying devices, the mechanical wear of the cargo conveying devices, the mechanical load action on the cargo items, the conveying time of the cargo items and the noise generation during the conveying of the cargo items.

A method for manufacturing a fuselage structural component (200) for a triangular section of an aircraft is disclosed, comprising the following steps: providing a one-piece sheet (211, 212, 213) of frame material, the sheet having an opening (250), and deforming at least one inner edge of the sheet (211, 212, 213) forming the opening (250) into an inner flange (215, 216, 217), and deforming at least one outer edge of the sheet (211, 212, 213) into an outer flange (214). The one-piece and deformed sheet (211, 212, 213) forms, adjacent to the opening (250), a frame section (210), a bottom support (212), and a vertical support (213).

A middle fuselage temporary protection floor comprises a splice plate body and a limiting block, a limiting groove is formed in the bottom face of one side edge of the splice plate body in the length direction of the splice plate body, a limiting block mounting groove is formed in the top face of the side edge, provided with the limiting groove, of the splice plate body, and a round hole is formed in the groove bottom of the limiting block mounting groove; two screw holes are formed in one side of the limiting block, a limiting metal block circular boss is arranged on the bottom face of the other side of the limiting block, the limiting block is arranged in the limiting block installation groove, the limiting metal block circular boss penetrates through the circular holes and protrudes out of the bottom face of the limiting groove, and the limiting block is locked in the limiting block installation groove in the mode that screws penetrate through the screw holes. The protective floor provides an operation platform for workers, meanwhile, the limiting block is arranged on the splice plate body, and the metal block circular boss on the limiting block is matched with an airplane passenger cabin seat sliding rail hole, so that the floor is prevented from moving out of a proper area.

A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

A fixed-wing cargo aircraft having a kinked fuselage is disclosed. The fuselage contains a continuous interior cargo bay, and includes a forward portion, an aft portion, and a kinked portion forming a junction in the fuselage between the forward and aft portions. The kinked portion contains a transition region of the cargo bay and defines a bend between a forward centerline and an aft centerline. The kinked portion is formed with a forward transverse frame section, a separate aft transverse frame section, and a plurality of longitudinal frame elements extending between the forward and aft frame sections, the forward frame being coupled to an aft end of the forward portion and the aft frame section being coupled to a forward end of the aft portion such that the aft frame section is angled with respect to the forward frame section about a lateral axis of the cargo aircraft.

An aircraft seat connector (40) for mounting an aircraft seat (20) to a mounting rail (17) provided at a floor of an aircraft cabin (16) is provided. The aircraft seat connector (40) comprises a base portion (42) for being introduced into the mounting rail (17) and a seat connection portion (50). The seat connection portion (50) extends from the base portion (42) and is configured for being releasably coupled to an aircraft seat (20). The seat connection portion (50) allows for coupling the aircraft seat (20) to the seat connection portion (50) in at least two different spatial orientations.

An apparatus fastens cabin components in a region of side walls, which belong to an aircraft structure and extend in a vertical direction in relation to a horizontal cabin floor. The apparatus includes a substructure, which includes: at least two supports, which are vertically arrangable on a side wall, of the sidewalls of the aircraft structure, are spaced apart in a horizontal direction, are designed in each case for fastening at at least two vertically spaced-apart defined points of attachment of the aircraft structure in the region of the side wall, and at least one panel, which connects the supports in the horizontal direction and is designed for connecting to the supports, each connected by the panel, at two vertically spaced-apart points of connection. Both the at least two supports and the at least one panel are designed in order for cabin components to be fastened thereon.

An access system for a vehicle includes a door (110) moveably coupled to a portion of a fuselage (106). The door (110) is configured to be moved between an open position in which an opening (108) of an internal chamber is opened, and a closed position in which the opening (108) of the internal chamber is closed. One or more actuators (112) are secured to the door (110). The one or more actuators (112) are configured to move the door (110) between the open position and the closed position.

To provide a nose landing device assembly used in a high blade machine for defining a nose device bay.SOLUTION: A nose landing device assembly includes an oleo-shock strut, and a front brace including a first end of a front brace and a second end of the front brace. The first end of the front brace is turnably coupled to a nose device bay around a first turning shaft. The assembly also includes a rear base including a first end of the rear brace and a second end of the rear brace. The first end is turnably coupled to the nose device bay around a second turning shaft, and the second end is turnably coupled to the oleo-shock strut. The actuator includes a first end of the actuator and a second end of the actuator. The second end is coupled to the nose device bay, and the first end is coupled to the front brace. The actuator is configured to move the nose landing device assembly between a retreat position and an extension position.SELECTED DRAWING: Figure 1

The present invention relates to a transport unit for consumer goods in a hold of an aircraft, comprising a base body with a top side and a bottom side, a plurality of roller elements projecting from the top side, connecting elements arranged at the front of the transport unit for the detachable connection of two transport units, and at least one non-slip element arranged on the bottom side.

The invention relates to a lateral guide (10) for guiding and / or securing cargo items, in particular containers and / or pallets, in an aircraft, comprising at least one lateral guide device (11) and at least one holding unit (12) for the lateral guide device (11), wherein the holding unit (12) comprises a longitudinally extending (v) mounting frame (13) and at least one locking device (14) arranged on the mounting frame (13), the locking device having a plurality of recesses (15) extending transversely to the longitudinal direction (v), wherein the lateral guide device (11) can be inserted into at least one of the recesses (15) at different positions (A, B, C, D, E) and can be locked in the inserted state at the different positions (A, B, C, D, E) by the locking device (14), wherein the lateral guide device (11) has at least one contact element (16).which, in the inserted state, can be brought into engagement with or is in engagement with at least one longitudinally displaceable fixing element (17) of the fixing device (14), wherein the fixing element (17) has at least one fixing contour (23) with which the fixing element (17) engages in a fixing position in the cross-sectional contour (22) of the opening (21) for fixing the side guide device (11) in a form-fitting manner, wherein the fixing contour (23) and the cross-sectional contour (22) are mushroom-shaped.

The invention relates to a fixed joint for an aircraft cabin floor, an aircraft floor mounting system, an aircraft floor arrangement, an aircraft and a method for providing a fixed joint for an aircraft cabin floor. The joint includes a primary connection stud and a secondary attachment joint member. The main connection stud includes a mounting foot region and a joint head region. The mounting foot region is configured to be fastened to a fastening point. The joint head region includes a protrusion. The secondary attachment joint component is configured to be mounted to the joint head region. The secondary attachment engagement member is positioned to the engagement head region in a positioning movement and locked in a locking movement to achieve positive fit retention. The secondary attachment engagement members include a first type of engagement member positioned in a first positioning movement and locked in a first locking movement and a second type of engagement member positioned in a second positioning movement and locked in a second locking movement different from the first locking movement.

Shock-resistant chamber wall for use on a ship comprising a wall panel extending vertically between an upper and a lower deck with flat wall sides oriented perpendicular to the decks, a floor profile with a vertical leg and a horizontal leg, which is firmly connected to a lower deck, wherein the wall panel is firmly connected to the vertical leg of the floor profile, means for vertical guidance which are connected to an upper deck and guide the wall panel, a shock-absorbing insert which is arranged between the wall panel and the upper deck.

A cargo system for an aircraft may include one or more of the following: a cargo deck configured for the receipt of bulk cargo, the cargo deck including at least one deck panel; and a cargo transport system including a track for moving a cargo container; and at least one floor fixture exposed on the cargo deck, where the cargo transport system includes an installed state and an uninstalled state, the track being secured to the floor fixture when the cargo transport system is in the installed state and the track being displaced from the cargo deck when the cargo transport system is in the uninstalled state.