Abstract: An aircraft, particularly an unmanned aircraft, has at least one weapons bay. At least one standardized equipment container can be inserted into the weapons bay.

Abstract: Floor modules of a cargo deck in a hull of an aircraft which comprise support devices for carrying functional elements, e.g. panels, roller conveyors or ball mats, are provided. The support devices are attachable in the hull of the aircraft directly or by way of intermediate elements. To improve stability at reduced weight, end support devices, as seen in the aircraft's longitudinal direction, have a thickness reduced in such a way compared to the other support devices of the floor module that only together with the end support devices of a floor module installed adjacently in the hull do they ensure a loading capacity that corresponds to at least the loading capacity of the other support devices.

Abstract: The present application describes a quick-change fastening system for demountably mounting an element to a fastening structure. The element comprises an engagement element that is designed to engage a bearing element of the fastening structure, wherein the element is hingeably held around the bearing element between a hooked-in position and a fastened position. The element further comprises a fastening element that can be affixed to a locking element of the fastening structure when the element is in its fastened position. The engagement element and the bearing element are designed such that along a hingeing movement of the element a form-fit connection is established when the element is in its hooked-in position, and that a force-fit connection is established when the element is in its fastened position.

Abstract: A flap simulator for an aircraft has a support with a handle. A first couple is on the support and is selectively engageable to a flap track for guiding an aircraft flap. A second couple is also on the support and is selectively engageable to a flap actuator for moving the aircraft flap along the flap track. The support may have an adjustment feature that allows a size of the second couple to be changed to accommodate the flap actuator. The support is apart from the aircraft flap.

Abstract: An ejection device for an aircraft hatch having at least one articulation hinge. The articulation hinge is provided with a lower element designed to be mounted in rotation on structure of the aircraft, and an upper element designed to be joined to the hatch panel. The lower element and the upper element are connected to one another in a reversible manner. The ejection device has guide means in which the upper element of the articulation hinge is engaged, to hold the upper element in the axis of rotation (A) of the lower element during the activation of the hatch. The upper element of the articulation hinge can be separated from the guide means beyond a critical swing angle, so that the upper element is separated from the lower element of the articulation hinge. The invention also concerns an ejectable hatch for an aircraft.

Abstract: A carriage and release system for stores (armaments such as rockets and bombs) on an aircraft includes a bracket adapted for attachment to the aircraft. A pylon is mounted on the bracket for movement in a pitch direction relative to the aircraft. A mechanism is provided to power the pitch movement and position it at a predetermined angle relative to the aircraft. A variety of stores carriers may be employed with the pylon. Subcarriages may also be mounted to the pylon for attaching additional stores carriers.

Abstract: A device for the releasable fastening of a component in an aircraft includes a component carrier with a base plane, wherein the component carrier comprises an installation state in which the base plane of the component carrier comprises an angle relative to the horizontal base plane of the aircraft, and wherein the component carrier is equipped to accommodate a component in a releasably affixed manner.

Abstract: A removable cargo pod for attachment to an aircraft fuselage; a mechanism in said pod to raise and lower it into and from engagement with the fuselage; and an open top so as to provide access to the interior while it is vertically displaced or removed from the fuselage.

Abstract: The invention is directed to an actuation system in an aircraft comprising a fuselage and a hinged tail section with at least one interlock component that engages a tail support, wherein the engagement of the tail support to the tail section enables the actuation system to operate. The actuation system pulls in, latches, and locks the tail section during closing of the tail section, and the actuation system unlocks, unlatches, and releases the tail section during opening of the tail section.

Abstract: In an adjustment device for the alignment of supporting parts pivotally accommodating the guide rails of a freight loading system on structures having inherent dimensional tolerances, in particular in an aircraft fuselage. Each supporting part is designed as a bearing insert that can be inserted in a bearing eye of a bearing block such that it cannot rotate. Each bearing insert has fitting surface sections separated from one another by planes of symmetry, and has at least one asymmetrically arranged axis accommodation.

Abstract: A system and method for integrating air and ground transportation of passengers and cargo. The system comprises a plurality of universal passenger containers. The system further comprises a plurality of universal cargo containers. An airplane is provided with a hollow fuselage adapted to be loaded with a plurality of passenger and/or cargo containers. A flatbed trailer can be provided to carry a passenger or a cargo container. A tractor vehicle can be provided to transport flatbed trailers between airplanes, locations within the airport, and points of origin and destination outside the airport complex. A system can be provided to load and unload passenger and cargo containers into and out of airplanes at the airport. A system is provided comprised of an airport complex including take-off and landing runways, taxiways, airplane staging areas, apparatus for detection of weapons in passenger and cargo containers, and air terminals with arrival and departure gates and baggage handling conveyors.

Abstract: An interior structure for a mobile platform is provided. The interior structure is constructed of a lightweight collapsible frame that can be reconfigured from a compact, substantially flat collapsed state to a non-compact, substantially sprawling expanded state. In the expanded state, the collapsible frame provides at least a portion of a structural load bearing frame for the interior structure. The interior structure additionally includes a plurality of interchangeable panels that attach to the collapsible frame to form interior surfaces of the structure. The panels form such things as the interior wall, ceiling and floor surfaces and can also include amenities such as shelves, lights, beds, closets, electrical outlets, Internet connections and entertainment equipment. The interior structure can be carried though the typical man-door of a mobile platform.

Abstract: A sensor-carrying pod which has middle and readily detachable end sections. The end sections are chosen from a suite of different end sections, depending upon the sensors used in a mission. The sections may include panels, or windows specifically transmissive to predetermined wavelengths, such as visible and IR. A deployment arrangement allows the pod to move horizontally and vertically, from an aircraft, into the airstream, and back again after a mission. The door of the aircraft is sealed around a component of the deployment arrangement to allow for pressurization of the aircraft for high altitude reconnaissance missions.

Abstract: A passenger airplane container system comprises a pod. The pod has a hollow generally cylindrical configuration. The pod further has a horizontal divider. The horizontal divider separates the pod into a passenger area and a baggage area. An airplane is provided. The airplane has a central pod receiving region with a closure device. The closure device is movable between an open orientation and a closed orientation. The open orientation so allows for the movement of a pod into the receiving region. The closed orientation securely encompasses the pod. In this manner the pod is securely contained for takeoff and flight and landing.

Abstract: An aircraft and method of manufacture therefor are provided. A fuselage is formed of composite materials and in at least two sections, each section having an integral, internal longeron spanning a length of the sections. The sections are connected by slidingly engaging a male dovetail connector on a longeron of one section with a female dovetail connector on a longeron of another section. Outer edges of the sections of the fuselage have tongue-and-groove connectors that engage to fasten the edges of one section to the edges of another section as the sections are slidingly connected. Fasteners are inserted through the longerons, and other fasteners are inserted through the connectors of the outer edges.

Abstract: An automated galley-cart storage system for use in a structure having a lower area and an upper level. The storage system includes a container (22) sized to hold a predetermined maximum number of galley-carts (20) in lateral rows. An equal number of cart pallets (34) are provided as well. Galley-carts are positionable on the pallets within the container. A cart elevator (64) is located within the container and is used to lift and lower cart pallets through an upright passage (60) connecting the container with the upper level. An elevated transfer system (36) is located within the container to move the cart pallets in a predefined pattern within the container. The pattern passes through the elevator. During use, an operator may retrieve unused galley carts from the container and store used galley-carts in their place.

Abstract: A hand-held computer that displays the aircraft floor plan with passenger and baggage compartments shown on a pad, with which a pilot can calculate the Center of Gravity (CG) of an aircraft by simply entering the load weights for different areas of an airplane. The floor plan can be changed for different aircraft. Next to each section of the plane is a button that, when pressed, allows a pilot to enter data for that section. As the pilot adds weight to each section, the computer can calculate the CG for the loaded aircraft. The computer can display the total weight, CG and other data related to the plane. The device can also printout the data for use as a manifest or for other documentation purposes. The device is the size and shape of a clipboard. In one version, the floor plan is fixed. In a second version, the floor plan can be changed for different aircraft.