Abstract: An aircraft cabin includes an upper deck, and a cargo area. The cargo area is configured to accommodate at least one passenger and is situated at a different level than the upper deck. An accessway provides access between the upper deck and the cargo area. The upper deck has, at least locally, a raised floor in the vicinity of the accessway so that at least one part of the cargo area has a ceiling height higher than the ceiling height of the rest of the area cargo.

Abstract: A step assembly installable in a structure such as a housing of an armrest assembly, the step assembly including a base attachable to the structure including a mounting plate having a low profile and a fixed receptacle to be received in the structure, a step plate pivotally attached along a first end to the base along a lower end of the receptacle, the step plate pivotable between a stowed position in which the step plate is housed within the fixed receptacle and a deployed position in which the step plate is outside of the fixed receptacle, the step plate having a first side for supporting a foot, and a release mechanism for releasing the step plate from the stowed position to the deployed position. The step plate deployed for use and concealed from view between uses.

Abstract: The disclosed embodiments herein are generally directed toward force-balancing mechanisms for weighted members and/or loads. According to one embodiment, the force-balancing mechanism includes at least one gear rack, at least one spring assembly comprising a spring member operatively connected to the at least one gear rack, a pinion gear intermeshed with the at least one gear rack; and a variable radius cam. Rotation of the cam causes the pinion gear to rotate to thereby in turn linearly drive the at least one gear rack and accumulate spring force of the spring member. The spring member may be a compression or a tension spring. Preferably, the spring member is a compression spring.

Abstract: A collapsible staircase is provided with a set of flat parts, with each of the parts intended to function as steps. Each flat part can be moved between a first position and a second position. All of the flat parts are substantially coplanar when the parts are in the first position, and the parts are disposed above each other and at a distance from each other when the parts are in the second position. A retractable holding handle is also provided and driven together with the flat parts.

Abstract: A step assembly for a vehicle can include a housing and a support member hingedly coupled to the housing with a shaft. A first locking feature can be associated with the housing while a second locking feature can be associated with the support member. A spring can be operably associated with the support member and the housing such that the spring can bias the second locking feature toward the first locking feature. The support member is configured to rotate between a stowed position and a deployed position. Further, the support member is configured as a step support and a hand hold device.

Abstract: A step (10) comprising a portable support assembly (30) having a vertical body (40) carrying a tread (31). The step includes at least two pegs (20) fastened to a fuselage (2). The body (40) includes one fastener orifice (50) per peg (20), said body (40) being carried by said pegs (20). The step includes at least one locking system (60) carried by said body (40) for automatically locking the position of at least one peg (20) in a fastener orifice (50), and manual unlocking means (86) connected to the locking system (60) for enabling the body (40) to be manually separated from the pegs (20).

Abstract: A step assembly for a vehicle can include a housing and a support member hingedly coupled to the housing with a shaft. A first locking feature can be associated with the housing while a second locking feature can be associated with the support member. A spring can be operably associated with the support member and the housing such that the spring can bias the second locking feature toward the first locking feature. The support member is configured to rotate between a stowed position and a deployed position. Further, the support member is configured as a step support and a hand hold device.

Abstract: A cockpit for an aircraft nose, the cockpit having a floor that acts solely as a floor for the crew to walk on and that is lower than the height of the cabin floor situated behind the cockpit. The cockpit also has a stair connected to the floor in order to enter and leave the cockpit. This arrangement enlarges the volume of the cockpit and enables equipment to be housed therein that previously used to be housed in the zone that is difficult to access that is situated under the cockpit and that also contains the bay for storing landing gear.

Abstract: Maintenance steps on helicopters (10) comprising a casing (1), integrated into a lateral shell of a fuselage of a helicopter (11) for access from outside and a step (2) being pivotably mounted in the casing (1). The invention relates as well to methods for mounting and dismounting of such maintenance steps.

Abstract: A passenger stairway, which may be integrated with an aircraft, contains at least one first stairway segment having a first plurality of steps and a receptacle device, and at least one second stairway segment having a second plurality of steps, which is insertable into the receptacle device, so that the first and second stairway segments come to rest lying one on top of another.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: The present invention relates to a foldable step unit (10) for a rotorcraft, the step unit being provided with a bottom step (16) and a stationary support (11) that is secured to the structure of the rotorcraft (2). The step unit (10) comprises a left side beam (14) and a right beam (15) hinged on said stationary support (11), said bottom step (16) being arranged on a left free end (14?) and a right free end (15?) respectively of the left and right side beams (14, 15) via a pivot pin (16?), drive means (18) for said step unit (10) and connected via at least one control means (21, 22) to at least one side beam (14, 15) enable said step unit (10) to be retracted into and extended from a housing (2) formed in the rotorcraft (1).

Abstract: A door opening and closing mechanism for opening and closing the door from the inside of a fuselage. A door pivotally supported at an opening portion of the fuselage includes first and second position restricting links each having one end pivotally supported on the fuselage with a door driving link having one end pivotally supported on the door. The other end of the second position restricting link is pivotally supported on a middle portion of the door driving link. The door opening/closing operation lever is provided at one end with a grip with the other end pivotally supported on the other end of the door driving link. The middle portion of the door opening/closing operation lever is pivotally supported on the other end of the first position restricting link. By pulling the grip toward the inside of the fuselage and thereafter pushing downward, the door can be closed.

Abstract: Maintenance steps on helicopters (10) comprising a casing (1), integrated into a lateral shell of a fuselage of a helicopter (11) for access from outside and a step (2) being pivotably mounted in the casing (1). The invention relates as well to methods for mounting and dismounting of such maintenance steps.

Abstract: An aircraft 1 comprises a walkway 11 moveable between a stowed position and a deployed position. The aircraft may be arranged such that the walkway, in the deployed position, defines a path, at least a portion of which extends from the fuselage at an angle, when viewed from above, of less than 90 degrees to the longitudinal axis of the aircraft. The walkway 11, in the stowed position, may be located at an angle, when viewed from above, of less than 80 degrees to the longitudinal axis of the aircraft. The opening 9 may be located in a region extending from 20% to 80% of the total cabin length. The walkway may be further moveable to a second deployed position.

Abstract: A cabin door assembly is provided for use with a pressurized aircraft. The assembly includes two door halves for engaging the fuselage of the aircraft. Structurally, each door half includes a waist section integral with an adjoining tapered section. Further, the assembly includes an activator that is mounted on the fuselage and attached to the door halves. Specifically, the activator is attached to each door half to concertedly move each door half between a closed configuration and an open configuration. In the closed configuration, the door halves are sealed to the fuselage and to each other for pressurization of the aircraft. In the open configuration, the door halves extend outwardly from the fuselage to allow for aircraft ingress and egress.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: The invention relates to a bearing application for staircases in an aircraft with at least two decks. According to the invention at least two bearings, each with at least partially different possibilities of movement about and along or parallel to the x-axis, y-axis and z-axis of a system of coordinates, are arranged on each staircase at the lower and upper staircase end (rotatory and/or translational movements). Due to the presence of at least four bearings on each staircase, the relative movements between decks can be compensated for. Consequently the static design of the staircases can be limited to the intrinsic weight and operation-related loads by the mass of the users, thereby providing weight savings.

Abstract: The present invention relates to a foldable step unit (10) for a rotorcraft, the step unit being provided with a bottom step (16) and a stationary support (11) that is secured to the structure of the rotorcraft (2). The step unit (10) comprises a left side beam (14) and a right beam (15) hinged on said stationary support (11), said bottom step (16) being arranged on a left free end (141) and a right free end (15?) respectively of the left and right side beams (14, 15) via a pivot pin (16?), drive means (18) for said step unit (10) and connected via at least one control means (21, 22) to at least one side beam (14, 15) enable said step unit (10) to be retracted into and extended from a housing (2) formed in the rotorcraft (1).

Abstract: A module for an aircraft for accessing an upper region of the aircraft includes both an ascent region and an accommodation region, with the regions being divided from each other by a divider element. The accommodation region may, for example, be designed as an on-board lavatory. In this way it may be possible to do without the provision of an additional lavatory monument.

Abstract: The present invention provides a stiffening element for stiffening a step-like substructure, in particular in an aircraft or spacecraft, having a foot section which is composed of a fiber composite material and is shaped in the form of a step such that it essentially fills the substructure. A method is also provided for production of a stiffening element for stiffening of a step-like substructure in an aircraft or spacecraft, according to which a profile part with a foot section which is composed of a carbon-fiber-reinforced plastic is provided, at least one layer of a glass-fiber-reinforced plastic is laminated onto the foot section, and the glass-fiber-reinforced plastic is milled corresponding to a step-like shape which essentially fills the substructure.

Abstract: This collapsible staircase is provided with a set of flat parts (6) each intended to function as steps. Each flat part (6) can be moved between a first position and a second position. All the flat parts (6) are substantially coplanar when they are in their first position, and are disposed one above the other and at a distance from one another when they are all in their second position. Advantageously, a retractable holding handle (44) is also provided and driven in movement together with the flat parts (6).

Abstract: An overhead area access staircase system (10) for an aircraft (12) includes an aircraft overhead module (20) and multiple stair segments (40). The stair segments (40) are actuated relative to each other when deployed and are configured to be in proximity with the overhead module (20). The stair segments (40) are in contact with the overhead module (20) when deployed. The stair segments (40) include step elements (42) and support members (44) coupled thereto.

Abstract: A mid-level deck is provided as part of a main passenger cabin of a commercial aircraft and includes an elevated platform between the cabin floor and ceiling to provide additional storage space and areas for use by crew members. The mid-level deck also facilitates access to overhead modules. The storage space is provided under the elevated platform for storing galley carts, bins or similar storage items. A plurality of different articles may be provided in conjunction with the mid-level deck and/or connected to the elevated platform, including extra seats, storage members and sleeping units. More than one mid-level deck may be provided within a single main passenger cabin and and/on different levels of an aircraft.

Abstract: Provided is a fabrication that is simple to make and cost effective in optimizing performance for moderately extended high velocity missions of high performance airborne vehicles. To counter rapid thermal loading while providing a relatively low cost structure, a laminate, in a preferred embodiment an intermediate modulus carbon fiber laminated as fabric layers in a resin matrix, is stitched through with glass fiber material. This laminate is then cured and formed as a section of skin of a supersonic missile, enabling extended supersonic operation, nominally some minutes after the laminate's Tg has been reached or exceeded. Additionally, an airframe and airframe members constructed in accordance with a preferred embodiment of the present invention are disclosed. Compared to existing materials, it reduces cost and weight, increases thermal stability, and maximizes internal payload.

Abstract: An aircraft having a cabin within a wing of the aircraft includes an access opening in an aft end of the cabin adjacent a trailing edge of the wing, and a trailing edge portion of the wing juxtaposed with the access opening and including at least one pivotable panel which is pivotable into an open position so as to form a passage in the trailing edge portion for entry therethrough and through the access opening into the cabin. The trailing edge portion in one embodiment comprises upper and lower panels which are normally in converging relation such that the passage to the access opening of the cabin is normally closed, but which are pivotable relative to each other for creating the passage. The lower panel preferably is pivotable into a generally horizontal position so that it serves as a ramp for loading and unloading persons and cargo into and from the cabin. The upper and/or lower panel in another embodiment may be pivoted during flight so as to serve as a control surface for the aircraft.