A system has a frame with first and second spaced apart edges, a first holder couplable to the fuselage structure and embodied for articulated connection to a first region of the frame that is close to the first edge, a second holder couplable to the fuselage structure, and a strut. A first end of the strut is connectable in an articulated manner to the second holder. A second end of the strut is connectable in an articulated manner to a second region of the frame near the second edge and remote from the first edge. The frame and the strut form a triangular structure with the first and second holders. The strut and the frame form two sides of the triangular structure. A length of the first and/or second side is variable to adjust the position of the frame.

A vehicle include an interior cabin including a plurality of structural components, a plurality of electrical devices within the interior cabin, a power supply, and an electrical signal distribution system mounted to at least one of the plurality of structural components and electrically coupled to the power supply and the plurality of electrical devices. The electrical signal distribution system includes a printed circuit board (PCB), and a plurality of outlets coupled to the PCB. The plurality of outlets electrically couple to the plurality of electrical devices. The electrical signal distribution system provides electrical signals to the plurality of electrical devices.

Described is an aircraft suite having an aircraft seat for use by a passenger, the aircraft suite also having a controller, for controlling a number of output states of the aircraft suite, the controller having a logic condition receiver for receiving a logic condition input, and distance measurement equipment for measuring a distance between a first location within the suite and a second location within the suite, and providing a distance input to a distance receiver of the controller, wherein, in use, the controller controls at least one of the output states of the aircraft suite based upon both the logic condition input and the distance input. The invention also provides a method of controlling an environment within an aircraft suite.

An implementation of a contoured class divider for dividing an aircraft cabin includes a panel positioned between an aft seat and a forward seat, the panel having an aft-facing convex contour closely matching an aft-facing contour of a seatback of the forward seat and configured to enhance space utilization. The contoured class divider may include an articulation system to articulate at least a portion of the panel from a first position (normal operation) to a second position (emergency landing). The contoured class divider may provide up to an additional 12 inches of space which can be used to reduce seat pitch (and thereby enhance passenger comfort) or increase the number of rows of seats on a given aircraft.

An aircraft seat for an aircraft passenger compartment suite may include a primary section with an upper actuatable portion and a lower actuatable portion. The primary section may be configured to actuate between a primary upright position and a primary lie-flat position. The aircraft seat may include an auxiliary section including an auxiliary seatback portion coupled to a privacy shell element of the aircraft passenger compartment suite and an auxiliary seat base portion configured to actuate between an auxiliary upright position and an auxiliary lie-flat position. The auxiliary seatback portion may include an actuatable element. The actuatable element may be configured to actuate between an open position and a closed position. The actuatable element may be configured to provide access to a stowage compartment when the actuatable element is in the open position.

An illuminated handle mounted to a surface of a crew work area includes an illuminated portion is disposed on an interior surface. A structural portion is integrated into work area stowage compartments, disposed between two stowage compartments, such that the illuminated portion illuminates the stowage compartments and their contents when opened. The illuminated handle includes an illuminated coat hook protrusion extending from a top portion of the illuminated handle. The illuminated portion of the illuminated coat hook is disposed on an interior surface to further illuminate the stowage compartments and indicate the location of the illuminated coat hook, while the hook extension prevents the illuminated portion from directly illuminating a crew member's face and potentially blinding the crew member momentarily.

An aircraft passenger compartment suite may include at least one single passenger compartment including at least one single aircraft seat. The at least one single aircraft seat may be configured to seat a single passenger. The aircraft passenger compartment suite may include a combined divan passenger compartment with a combined divan aircraft seat. The combined divan aircraft seat may be configured to seat at least one passenger. The combined divan aircraft seat may have a width greater than a width of the at least one single aircraft seat. The combined divan passenger compartment may include a stowage compartment configured to stow large passenger amenities in a substantially vertical orientation. The aircraft passenger compartment suite may include a privacy divider separating the combined divan passenger compartment and the at least one single passenger compartment.

Systems and methods relating to foreign object detection with respect to passenger-accessible stowage compartments are provided. According to one example, sensor data is captured via a sensor subsystem that includes a sensor associated with each of a plurality of stowage compartments. For each of the stowage compartments, a baseline condition is identified in which foreign objects are absent from the stowage compartment. A foreign object is detected within a stowage compartment based on the sensor data received for the stowage compartment and the baseline condition identified for the stowage compartment. An audit of the stowage compartments is conducted, and based on the audit, an indication that the foreign object is detected within the stowage compartment is output. This indication may identify the stowage compartment containing the foreign object among the plurality of stowage compartments.

In passenger aeroplanes, baggage compartments for holding passengers' baggage are usually arranged above the rows of seats. The present invention proposes an interior space management system which is characterized by improved management of the aeroplane interior. For this purpose, an interior space management system (1) for an aircraft (2) is proposed, the aircraft (2) having a stowage compartment arrangement (6), the stowage compartment arrangement (6) having a plurality of stowage compartment sections (7), each for holding one or more baggage items (8), and having a control unit (16), the control unit (16) being designed to control and/or manage a distribution of interior regions of an interior space (3) of the aircraft (2), and the control unit (16) being designed to control and/or manage an occupancy of the stowage compartment sections (7) on the basis of historical data of the aircraft (2) and/or on the basis of baggage data of the baggage items (8).

A retaining assembly and method for use within an internal cabin of an aircraft, in which the retaining assembly includes a hinge including a biasing member. The hinge is moveable between a retaining position, in which the biasing member is configured to exert a biasing force into a top surface of a ceiling panel within an internal cabin of a vehicle to prevent the ceiling panel from upward motion, and a release position, in which the hinge is configured to be pivoted away from the ceiling panel and the biasing member is configured to be separated from the ceiling panel.