241results 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 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.

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.

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 (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 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 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.

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.

The utility model belongs to the technical field of machine manufacturing, and relates to a floor seat nest protection device. The device is formed by combining a first protection piece and a second protection piece, the upper end face of the first protection piece is of a square or circular structure, and a first plug is arranged on the lower end face of the first protection piece; the upper end face of the second protection piece is of a circular arc and square combined structure, and a second plug is arranged on the lower end face. And the first plug and the second plug are respectively matched with seat nests at corresponding positions on the machine body in a plugging manner. The seat pit can be effectively protected, the protection piece has the advantages of being light in weight and low in material and machining cost, the maintenance period can be shortened, and cost is reduced.

An aircraft (10, 10") has an aft main cargo cabin (50) with a low deck floor (52), and a rear access (60) configured to provide access to the aft main cargo cabin from behind the fuselage (20). The deck floor of the aft main cargo cabin is lower than a first deck floor (32) of a forward main cabin (30) of a forward section of the fuselage. The aft main cargo cabin has a second height (H2) that is greater than the first height (H1) of the forward main cabin, allowing the aft main cargo cabin to accommodate oversize cargo with larger dimension(s). The aircraft may be built with such an aft main cargo cabin and rear access, or may be a modified aircraft that includes such an aft main cargo cabin and rear access. Related methods of reconfiguring a base aircraft into a modified aircraft having such an aft main cargo cabin and rear access are also disclosed.

A pallet hold-down system having a horizontal and vertical movement securement apparatuses and a method of using the system where a rotatable member is interconnected with a vertical and a horizontal movement securement apparatus such that rotation of the rotatable member simultaneously locks both the vertical and horizontal movement securement apparatuses to prevent horizontal and vertical pallet movements.

The present invention provides a protective assembly for use in an aircraft cargo hold, comprising: a plurality of connectors, each of which is fixedly attached to the aircraft fuselage structure; a barrier wall, the barrier wall being movably connected to at least a portion of the plurality of connectors via couplings on its top and bottom sides; wherein each coupling comprises: a first tab disposed on the top or bottom side of the barrier wall, the first tab having an oblong hole extending vertically therein; a second tab disposed at the connector; a spherical bearing disposed in the second tab; and a bolt member, the bolt member being inserted through the spherical bearing in the second tab and the oblong hole in the first tab and being capable of moving vertically within the oblong hole. The protective assembly of the present invention does not participate in the transmission of loads from the main fuselage structure, is easy to assemble and disassemble, and has good reliability and maintainability.

The invention relates to a transport aircraft with an electric propulsion system and a fuselage section including a fuselage tube section (22) for hosting payload and battery packs comprising • a cabin floor separating an upper compartment from a lower compartment, • a plurality of floor beams extending in transverse direction for supporting the floor, separated in longitudinal direction from each other, • fuselage frames (221) supporting the cabin floor and / or the floor beams and / or the fuselage skin separated in longitudinal direction from each other, characterised in that the lower compartment is comprising a plurality of battery compartments separated in longitudinal direction from each other, each configured to host at least one battery pack, wherein the battery packs are suspended from the floor beam and / or floor. Advantages: Based on an aircraft 10 to carry passengers, with an electric or hybrid propulsion system. The fuselage is sized in a conventional single-aisle or widebody configuration. At least one fuselage tube section host in the lower compartment a plurality of battery compartments to hold battery packs for the electric propulsion unit. Since the battery packs are suspended from the floor beams the fuselage can sustain deformation from crashes with reducing the risk of fatal battery damages.

A profile rail for a floor of a vehicle has a base made of a first material and a top portion exposed during use of the profile rail in the floor of the vehicle. The top portion has a cold sprayed coating of a second material that is at least one of harder, more wear-resistant, or less corrosive as the first material. The top portion has a seat rail crown having a first hook element produced entirely from the second material.

A rail for the fastening of equipment elements, such as, in particular, seats, in aircraft, includes a holding region for connection to an equipment element of an aircraft, and a support region to fasten the rail to a carrier element of the aircraft. The rail has a metallic shell which is, for example, made of titanium and which is filled with a fiber-reinforced thermoplastic filler material which is reinforced by short fibers. To produce the rail, a metallic molded part is used as a casting mold and is filled, for example by injection, with the filler material and, after the rail has been produced, forms the metallic shell for the filler material.

The unfaired aeronautical propulsion system comprises a propeller extending around a main axis and having at least one variable-pitch rotor blade around a rotor pitch axis. For each variable-pitch rotor blade, the relative position of maximum thickness (x°_EPmax) decreases from a first relative height (R1) between 20% and 40% to a second relative height (R2) between 55% and 100%, where the relative position of maximum thickness (x°_EPmax) is between 15% and 35%, preferably between 20% and 30%. (See Figure 5 for abbreviations.)

(DE) The present invention relates to a transport drone with a main body having a wing at its upper part and a transport compartment at its lower part, through which a transport object, for example a car, can be inserted and removed forwards and backwards; and a buoyancy element with several tubes connected to the lower part of the main body and which are inflatable and deflatable by means of air pressure. In this configuration, the tubes, which expand and contract by means of air pressure, are connected along the lower perimeter of the main body. By means of the sequential expansion and contraction of the tubes, the drone can not only land on the water surface by means of the buoyancy force, but also, if it tips over on the water surface, hover above the water surface by means of the sequential expansion and contraction of the tubes, thus preventing it from falling into the water.

Guidance system for a vehicle seat and vehicle comprising such a system The present invention relates to a guidance system for a vehicle seat, comprising a rail (32) extending on a floor (13) of the vehicle in a longitudinal direction (X), the rail comprising a groove (36), an upper opening (38) extending along the groove, two plates (41a, 41b) provided with a plurality of receiving orifices (43a, 43b), and comprising a device (70), arranged in the groove (36).The equipment further comprises a locking device (76) comprising a locking plate (78), movable in translation relative to the carriage (65) in a height direction (Z), located between the support plate (74) and the upper opening (38), and a plurality of pins (79a, 79b), fixed on the locking plate, the locking device being configured to evolve between a locked configuration, in which each pin is engaged in one of the receiving orifices and a free configuration. Figure for the abstract: 4.

An aircraft panel removal tool and work aid is disclosed. The tool comprises an anchor attachment fitting. The attachment fitting includes a plurality of claws that are biased open and configured to engage an attachment point of an aircraft component anchor. The attachment fitting also includes a collar slidably disposed over and about the plurality of claws. The collar slides upward to enable the plurality of claws to open and be disposed around the attachment point of the aircraft component anchor. The collar then slides downward to engage the plurality of claws with the attachment point of the aircraft component anchor. The tool includes a handle secured to the attachment fitting and configured to enable removal and / or manipulation of the aircraft panel.

The present invention makes it possible for various flying devices to land.　A takeoff / landing device (91) for a flying device (3) comprises a first support part (92A) that can support at least a portion of the flying device (3) and a second support part (92B) that can support at least a portion of the flying device (3) and, with the first support part (92A), is to support the flying device (3) to allow the flying device (3) to take off and land. The first support part (92A) and the second support part (92B) are separated in the horizontal direction, and the space between the first support part (92A) and the second support part (92B) is unobstructed in the vertical direction.