A container assembly configured for loading into/onto a Unit Load Device (ULD) generally includes a first container, second container, and a base support member having a wedge abutment assembly. Rearward sides of the first and second containers include a securing catchment assembly for drawing, mating, and securing the rearward sides of the first and second containers to one another. Frontward sides of the first and second containers each include a plurality of female/male fastening assemblies that complementarily mate and draw the frontward sides of the first and second containers toward one another. During loading, an inwardly angled surface of the wedge abutment member causes the second container to be directed toward the first container.

A method for integrating and fitting at least one item of equipment and/or at least one line in a technical bay of an aircraft, comprising the steps comprising attaching the equipment and/or the line(s) on an integration module outside the fuselage of the aircraft, introducing the integration module into the fuselage of the aircraft via an opening of a baggage hold, and securing the integration module to a structure of the aircraft. An integration module is provided which comprises a chassis bounding a volume in which are positioned and attached at least one item of equipment and/or at least one line and having a cross section that is approximately identical to that of a baggage container and a length which is less than or equal to that of a baggage container.

A latch assembly may comprise: a housing; a pawl assembly coupled to the housing, the pawl assembly configured to transition from an un-restrained state to an restrained state; and a latch state detection system comprising a transducer and a communications module, the transducer configured to convert mechanical energy from the pawl assembly reaching the restrained state to an electrical energy configured to power the communications module.

A cargo restraint includes a housing. The cargo restraint further includes an inner pawl and an outer pawl coupled to the housing and configured to rotate between a retracted position and an erected position relative to the housing. The cargo restraint further includes a locking pawl rotatably coupled to at least one of the inner pawl or the outer pawl and configured to rotate between a locked position in which the inner pawl and the outer pawl are locked in the erected position and an unlocked position.

A restraint for use in restraining cargo includes a main body having an elongated shape with a contact end configured to contact and restrain the cargo and a second end opposite the contact end, the contact end defining a first face and a second face such that a first angle between the first face and the second face is at least one of less than or equal to 160 degrees. The restraint further includes a spring configured to allow the main body to rotate relative to a stationary object in response to contact with the cargo and to cause the main body to return to a neutral position in response to a lack of contact with the cargo.

A quick-connect fitting for a convertible cargo handling assembly may comprise a fixed portion and a coupling component. The fixed portion may be secured to an aircraft frame structure. The coupling component may be coupled to a removable cargo handling component. The coupling component may be configured to rotate relative to the fixed portion.

A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.

The invention relates to a payload monitoring system of an aircraft, wherein the system comprises at least one storage area (26, 28, 30, 32, 36, 38, 42) for a payload and at least one pressure sensor (10), wherein the at least one sensor (10) is configured to detect a weight force and its center of gravity of payload resting on the storage area (26, 28, 30, 32, 36, 38, 42). Furthermore, the invention relates to an aircraft and a method for operating an aircraft.

A cargo deck for an aircraft having a center plane extending centrally along a longitudinal direction of the cargo deck. The cargo deck includes one or more perforated rails spaced apart from the center plane. The perforated rails may be arranged parallel to the center plane. The cargo deck may also include one or more roller tracks and/or fitting elements arranged relative to the center plane. The cargo deck may also include a one or more center guide locks having one or more guide claws.

Systems and methods are described for securely monitoring a shipping container for an environmental anomaly using elements of a wireless node network of sensor-based ID nodes disposed within the container and a command node associated with the container. The method has the command node identifying which of the ID nodes are confirmed as trusted sensors based upon a security credential specific to each of the ID nodes; monitoring only the confirmed ID nodes for sensor data broadcast those ID nodes; detecting the anomaly based upon the sensor data from at least one of the confirmed ID nodes; automatically generating an alert notification related to the detected environmental anomaly for the shipping container; and transmitting the alert notification to the external transceiver to initiate a mediation response related to the detected environmental anomaly.