A curtain track for an aircraft cabin enables curtain sliders to be quickly loaded into the curtain track. The curtain track is constructed of an elongate channel with a first end fitting on a first end of the channel and a second end fitting on a second end of the channel. There is a unique cutout in the bottom surface of the first end fitting that forms a curved slot surface that enables curtain sliders to be loaded into the channel of the curtain track through the cutout to quickly load the curtain onto the curtain track without disassembling any of the parts of the curtain track or removing the curtain track from its attachment to the aircraft cabin.

A separating element for a platform cabin comprises at least one leaf subjected to a return force toward its open position, and, for the or each leaf, a return member for returning the leaf toward its closed position and comprising a first end articulated at an articulation point movable jointly with the leaf. This return member also comprises a second end mounted movably relative to the partition between an active position and an inactive position, such that when the leaf is open and the second end is in the active position, the return member exerts, on the leaf, a return force returning the leaf toward its closed position, and when the leaf is open and the second end is in the inactive position, the return member is in a second configuration in which it does not exert a force returning the leaf toward its closed position.

A static aircraft seat privacy panel may include a body. At least a portion of a surface of the body may be shaped to at least partially conform with at least a portion of an aircraft seat. A lower edge of the body may be configured to couple to a floor via a set of floor-mounted components. The set of floor-mounted components may be within the floor separate from a set of seat tracks of an aircraft seat compliant with 16G force requirements for aviation transport. An upper edge of the body may be configured to be offset a selected distance from a surface of one or more overhead structures of the aircraft cabin when the body is coupled to one or more structures positioned proximate to a ceiling of the aircraft cabin. The static aircraft seat privacy panel may be compliant with 9G force requirements for aviation transport.

A computer-implemented method for space frame design involves constructing a load stress map in a geometrical boundary representation of a design space, defining attachment points and load application points in the design space, creating a starting network of interconnecting lines between each two of the attachment points and load application points in the design space, assigning load application factors to each line of the starting network of interconnecting lines based on values of the load stress map, generating potential space frame designs by culling different subsets of lines of the starting network of interconnecting lines for each potential space frame design according to variable culling parameters, evaluating the potential space frame designs with respect to optimization parameters, combining the culling parameters for the potential space frame designs the performance score of which is above a predefined performance threshold, and iterating the steps of generating potential space frame designs and evaluating the potential space frame designs on the basis of the combined culling parameters.

A bulkhead assembly for an aircraft passenger cabin having a floor and a secondary support member includes upper and lower bulkhead panels and a bulkhead coupling member. The upper bulkhead panel defines an elongated tower portion that protrudes through a slot opening in an overhead closeout panel, and directly or indirectly connects to the secondary support member. The lower bulkhead panel connects to the upper bulkhead panel and to the floor via the bulkhead coupling member. A method for installing the bulkhead assembly in the passenger cabin includes connecting the lower bulkhead panel to the floor, joining the lower bulkhead panel to the base of the upper bulkhead panel using a bulkhead coupling member, inserting the terminal end through the slot opening, and connecting the terminal end to the secondary support member behind the overhead closeout panel.

A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

A dual-occupancy aircraft minisuite incorporating a modular multiple-egress door assembly is disclosed. In embodiments, the dual-occupancy minisuite can accommodate two passengers in enhanced privacy. Access to (and egress from) the minisuite is through the modular multiple-egress door assembly, which provides forward and rear (relative to the egress gap between) sets of outer, intermediate, and inner doors. The outer doors translate laterally along rails in the intermediate doors, and the intermediate doors likewise translate laterally along rails in the inner doors, to open the minisuite for passenger access or direct view (or to close the minisuite for enhanced privacy). The forward and rear sets of doors are proportioned such that when any forward or rear translating door is jammed in a closed position, the remaining egress gap is of sufficient width to provide a distinct and independent emergency egress path for each occupying passenger of at least minimum required width.

A redundant rail and carriage assembly is disclosed. The assembly may include a primary sub-assembly including a primary rail and a primary carriage. The assembly may include a secondary sub-assembly including a secondary rail and a secondary carriage, the secondary rail being different than the primary rail, the secondary carriage being different than the secondary carriage. The assembly may be configured to couple to an actuatable door configured to actuate between a stowed door position and a deployed door position via at least one intermediate door position using one of the primary sub-assembly or the secondary sub-assembly, the secondary sub-assembly being configured to actuate the actuatable door via the secondary rail and the secondary carriage if one of the primary rail or the primary carriage of the primary sub-assembly fails.

A carriage slider and rail assembly is disclosed. The assembly may include a linear rail including one or more surfaces that define a channel. The assembly may include a carriage slider sub-assembly. The sub-assembly may include a slider configured to be axially displaceable within the channel of the linear rail. The sub-assembly may include one or more overload protection lobes including a first overload protection lobe positioned adjacent to a first end of the slider and a second overload protection lobe positioned adjacent to a second end of the slider. The sub-assembly may include one or more friction reducing portions. The overload protection lobes may make contact with the channel of the linear rail when an abuse load is applied to provide overload protection. The overload protection lobes may be configured to not make contact with the channel of the linear rail when an abuse load is not applied.

The present invention provides an aircraft passenger accommodation unit comprising a seat, a shell that allows a passenger egress between an aisle and the seat through an opening, and a door assembly comprising a door slidable with respect to the shell between a retracted position and an extended position, a slide track attached to the shell, a slide runner for sliding along the slide track, and a connection mechanism for selectively connecting the door to the slide runner, wherein the door has a first sliding mode in which the connection mechanism connects the door to the slide runner and wherein the slide runner slides along the slide track, and a second sliding mode in which the connection mechanism does not connect the door to the slide runner and wherein the door slides in relation to the slide track. The invention also provides a door arrangement and associated methods.