Abstract: An integrated cargo loading and video monitoring system for an aircraft having at least one cargo compartment is disclosed. The system includes a cargo loading processor and a plurality of power drive units within the cargo compartment, each power drive unit being coupled to the cargo loading processor. The system also includes a video processor, and at least one video camera within the cargo compartment, the camera being coupled to the video processor. A central processor in communication with the cargo loading processor and the video processor is operable to receive information from both the cargo loading processor and from the video processor.

Abstract: A floor panel assembly, system, and method for assembling a floor panel assembly and one or more floor beams are provided. A floor panel assembly may include a floor panel comprising a pair of opposed surfaces, wherein the floor panel includes at least one key hole slot defined in one of the opposed surfaces. The assembly also includes at least one seat track positioned between the opposed surfaces, wherein the seat track comprises at least one key hole slot defined therein that is substantially aligned with a respective key hole slot defined in the floor panel. In addition, the assembly includes at least one fastener assembly comprising a fastener configured to be positioned through a respective key hole slot defined in the floor panel and the seat track.

Abstract: A pallet system includes a pallet upon which cargo or other payloads may be carried. The pallet has a plurality of tie-down locations at which the pallet may be tied-down on a base, and at least one tie-down device for tying down the pallet on the base at any of the tie-down locations. The pallet further includes means for mounting the tie-down device on the pallet at any of the tie-down locations.

Abstract: A cargo roller tray shear fitting that may be used to fasten a cargo roller tray to a floor beam. The shear fitting may include a back plate having at least one slot. A lug extends from the back plate and has a lug opening.

Abstract: The invention relates to multi deck passenger aircraft, having passenger cabins and/or service facilities arranged on the upper and lower deck and inner load bearing cell structure provided within aircraft body. The present invention is also directed toward methods for manufacturing derivative multi deck aircrafts. Energy absorbing, floatable cargo containers (24) attached to fuselage belly. External fuel tanks (26) displaced on the top of fuselage. Center wing region of the fuselage is using for arranging rows of seats and service facilities. Addition seating configuration for narrow and wide bodied aircraft is provided. Multi deck seating configuration significantly reduces per passenger operating cost over existing technology. Less fuel per passenger is required since there is less airframe weight and wetted area per passenger. Due to the lower overall cost per passenger seat within the multi deck seating structure, the net profit and return on investment in the aircraft are also increased.

Abstract: A pivot system for a stowage compartment system for a mobile platform (for example, commercial aircraft) is provided. The pivot system includes a first fitting that defines a raceway and an engagement feature and a second fitting. The second fitting includes a hub for engagement with the raceway and a mating engagement feature to secure the first fitting within the second fitting. The second fitting also includes a guide that directs the first fitting into the second fitting to couple the first fitting to the second fitting.

Abstract: A device for locking containers into place includes a frame, at least one locking claw affixed to the frame, and an adjustment component which is affixed to the locking claw. A position of a container to be locked into place is adjustable relative to the locking claw in a longitudinal direction of the frame.

Abstract: An aircraft including a fuselage including a cabin to accommodate persons and/or a load, and a propulsion system. The propulsion system includes at least one tank and/or one combustion chamber, wherein part of the propulsion system can be used as an extension of the cabin to accommodate persons and/or a load, the part of the propulsion system lying adjacent the cabin and separated from the cabin by a partition.

Abstract: In one embodiment, a method of operating an aircraft having a passenger cabin and a cargo hold, comprises the steps of directing passengers to board the aircraft, directing passengers to deposit their luggage in a luggage deposit location on-board the aircraft, and subsequently taking the deposited luggage from the luggage deposit location and then storing the luggage in the cargo hold of the aircraft. In another embodiment, a method of unloading an aircraft having a cargo hold and a passenger cabin, comprises the steps of transporting items of luggage from the cargo hold to a luggage collection location on-board the aircraft, and directing passengers to collect their luggage from the luggage collection location and to disembark the aircraft is also provided. Information may be gathered with regard to the identity of passengers embarking and disembarking the aircraft. Yet another embodiment relates to an aircraft having a passenger cabin, a cargo hold, and a luggage handling system mounted in the cargo hold.

Abstract: The invention relates to floor heating for an aircraft which has a floor (20) made up of heatable panels (18). In order to be able to heat up the panels (18) in an energy-saving way, the same are provided with hollow chambers (26) which pass through them, wherein a feed line (28) for warm waste air originating from the cooling of the aircraft's electronic equipment which is connected to the first hollow chambers (26), conveys hot air to the first hollow chambers (26) when the floor heating system is in operation.

Abstract: A device for keeping objects, especially luggage, in an aircraft hold, the device including a flexible partition and at least one winding mechanism. The flexible partition is mounted on the winding mechanism such that it can be both wound onto the winding mechanism or unwound from the winding mechanism. The flexible partition includes an attaching mechanism that operates with a complementary mechanism to maintain the flexible partition in an unwound position.

Abstract: A self-adjusting loading guide and restraint for guiding and restraining aircraft unit load devices includes a base and an arm substantially upwardly extending from the base. The arm includes a vertical restraint portion and guide member having at least one substantially planar guide surface that is pivotally connected to the arm, and is movable between a first guide position and a second guide position. When the vertical restraint portion is engaged with a stowed first unit load device, the guide member assists in guiding a second unit load device away from the first unit load device and the loading guide and restraint and into a stowage location that is adjacent to the first unit load device.

Abstract: A roll-on/roll-off, aircraft-borne sensor pod deployment system having an operator station and a sensor pallet system and method of using same. The operator station has a base platform, a shelter box mounted on the base platform for accommodating a human operator, and a computer installed inside the shelter box. The sensor pallet system has a base platform, a linear system mounted on the base platform, a rotational system mounted on the linear system, a mechanical arm attached to the rotational system, a sensor pod attached to the mechanical arm, and an electrical control system that provides power to the deployment system and controls movements of the sensor pallet system. In operation, the sensor pod can be retracted into a compact, stowing position, or extended out an opening in the aircraft for an unobstructed field of view. The deployment system optionally includes an apparatus and method for sealing the aircraft opening.

Abstract: A roll-on/roll-off, aircraft-borne sensor pod deployment system having an operator station and a sensor pallet system and method of using same. The operator station has a base platform, a shelter box mounted on the base platform for accommodating a human operator, and a computer installed inside the shelter box. The sensor pallet system has a base platform, a linear system mounted on the base platform, a rotational system mounted on the linear system, a mechanical arm attached to the rotational system, a sensor pod attached to the mechanical arm, and an electrical control system that provides power to the deployment system and controls movements of the sensor pallet system. In operation, the sensor pod can be retracted into a compact, stowing position, or extended out an opening in the aircraft for an unobstructed field of view. The deployment system optionally includes an apparatus and method for sealing the aircraft opening.

Abstract: This application describes a floor segment (11, 13) for a means of locomotion, in particular for an aircraft, for the spatial separation of an interior space of the means of locomotion into a lower space (70) and into an upper space (60). The floor segment (11, 13) comprises an upper partition (81) and a lower partition (82), which together with the upper partition encloses a hollow space (30), which is equipped for accommodating system components (20-29, 32-35) of the means of locomotion. Preferably the floor segments are of a modular design so that within a floor (80) individual floor segments (11, 13) can be exchanged for other floor segments (11, 13) that comprise identical or compatible dimensions and connections for the system components.

Abstract: Devices, systems and methods are disclosed which relate to providing wing designs with payload integration capabilities on existing modularly assembled unmanned aerial vehicles (UAVs). Exemplary embodiments of the present invention present a novel technique of adding payloads to existing UAVs while improving flight performance over existing techniques by maintaining a similar overall weight with improved aerodynamic properties. The technique includes using a reinforced foam core center wing with a fiberglass epoxy skin. A lightweight payload canopy cover integrates onto the center wing as an agnostic enclosure for payloads. The payload canopy cover may contain venting holes for the cooling of electronic payloads. The systems may also include common devices such as antennas, GPS, and batteries for use with a wide range of payloads.

Abstract: In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight.

Abstract: An aircraft including a fuselage that includes a floor extending in the longitudinal plane of the fuselage and separating a first space from a second space accommodated in the fuselage. The first space includes a fuselage portion having a length essentially equal to the width of the floor along the fuselage cross-section, and the distance between the fuselage portion and the floor is essentially constant along the width.

Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.

Abstract: A wing for an aircraft having at least one weapon, and a feed duct for feeding the weapon with ammunition supplied in the form of a belt; the wing has a compartment for housing a portion of the belt and connectable to a loading opening of the feed duct.

Abstract: A baggage bin for an aircraft includes a compartment with a lower face substantially plane and a first flap that, in a closing position, is inclined toward the inside of the baggage bin in relation to a plane perpendicular to the lower face of the baggage bin. The first flap is mounted pivoting around a first axis. The bin includes a second flap arranged outside the first flap in relation to the baggage bin and articulated with the first flap. The second flap extends, in the closing position of the baggage bin, from a lower edge of the baggage bin to a ceiling edge.

Abstract: The present invention provides a combination ventilation and stowage bin system including at least one support duct defining an inlet for receiving conditioned air from a supply duct and an outlet for directing air into a passenger compartment, and a stowage bin for stowing luggage mounted to and supported by the at least one support duct.

Abstract: Roller modules have roller assemblies that are retractable below a cargo floor. Each module includes a housing, at least one roller for engaging cargo on the floor and, a mechanism mounting the roller on the housing for shifting movement between an extended position in which the roller extends above the floor for engaging cargo, and a retracted position in which the roller is disposed below the floor.

Abstract: A locking device for fastening containers for an aircraft. The locking device comprises at least one locking arrangement that can be affixed to an aircraft floor and that comprises a retaining element. The locking arrangement can be fastened to the aircraft floor such that a gap for adjusting the container is provided between the container and the locking arrangement. The retaining element of the locking arrangement can subsequently be moved in the direction of the payload such that a gap between the locking arrangement and the payload can be adjusted.

Abstract: A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention.

Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear delta wings, vertical winglets, and three levels. The fuselage has a cross-section of substantially rectangular flat shape, being is wide enough to provide lifting force, and includes three levels separated by multi-partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear delta wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at wingtips of the rear delta wings. The first level disposed at a bottom of the three levels includes a cargo bay and a plurality of landing gear bays. The second level disposed at a middle of the three levels includes fuel tank storages. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force.

Abstract: A fairing includes three sections: an aft section, a middle section, and a nose section. The aft section includes a first surface having a generally constant conic angle (i.e., a “boat-tail angle”) with respect to the longitudinal axis such that the aft section tapers to a first end configured to attach to a generally cylindrical body. The middle section, which intersects and is axially aligned with the aft section, has a second surface characterized by a constant elliptical cross-section along a plane orthogonal to the longitudinal axis. The nose section intersects and is axially aligned with the middle section. The nose section is further defined by four generally concave trianguloid surfaces, each extending from the middle section to a common apex intersecting the longitudinal axis, wherein each adjacent pair of trianguloid surfaces intersects at an edge (e.g., an incurvate edge).

Abstract: A cargo loading system capable of retaining a pallet along a centerline of a cargo aircraft and outside the wingbox area of the aircraft includes a number of devices. Included among these are first and second centerline end restraints mounted on the centerline, at least one caster panel mounted on one side of the cargo hold and across the centerline from a side door of the aircraft, and a plurality of mechanical restraints mounted on a floor of the cargo hold on either side of the centerline and outside the wingbox area. The first and second centerline end restraints each have at least one retractable lockhead configured and dimensioned to engage an end of a pallet. The at least one caster panel includes at least one retractable guide formed at a first end thereof, and at least one retractable guide formed along a first side thereof.

Abstract: A rib bay platform for use in an aircraft rib bay, is adjustable in length (for example it comprises two telescopically mounted sections. The platform comprises a first end configured for mounting on a stringer of the rib bay (for example by an interference fit), and a second end configured for mounting on another stringer of the rib bay (for example on feet mounted on ball-and-socket joints). A method of operating in an aircraft rib bay comprises the steps of providing a rib bay platform of adjustable length; adjusting the length of the platform; mounting the platform between the two stringers; whereby a person may then operate inside the aircraft rib bay whilst being supported on the platform.

Abstract: An exemplary, non-limiting swivel fitting attachment apparatus includes a ball fitting and a swivel fitting. The ball fitting includes a base having an attachment portion, such as a flange, arranged for attachment to a structure and a ball attachable to the base. The ball may be removably attachable or fixedly attached to the base. The swivel fitting has a first end having a socket portion that is arranged to receive the ball therein and a second end having an attachment portion that is arranged for attachment to an object. The socket portion of the swivel fitting may be expandable and closeable over the ball, and may include first and second socket portion members that are urgeable toward and away from each other. The second end of the swivel fitting may be couplable to a clevis fitting.

Abstract: An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft, includes selecting a passenger aircraft, and converting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo. The selecting step may involve an all-passenger aircraft, and the converting step may include removing all seats from the aircraft. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft includes aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. A converted cargo aircraft includes an aircraft body, and aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door.

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: An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft, includes selecting a passenger aircraft, and converting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo. The selecting step may involve an all-passenger aircraft, and the converting step may include removing all seats from the aircraft. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft includes aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. A converted cargo aircraft includes an aircraft body, and aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door.

Abstract: The invention relates to an assembly for storing objects in the cabin of a vehicle, comprising at least one frame with attachment means, and at least one holding device for mounting the objects, wherein the frame has a contour that, at least in some regions, essentially corresponds to the interior contour of a storage container so that the frame can be arranged in the storage container and can be attached in the storage container with the use of the attachment means, and wherein the holding device can be removably stored in the frame. The assembly according to the invention can be placed in a pre-assembled state in the vehicle, thus reducing the time required for installation and maintenance, while at the same time making better use of the available space.

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: An apparatus for attachment of a unit to attachment devices in a vehicle, in particular an aircraft, has attachment elements which are provided for connection to the attachment devices. In this case, at least one attachment adapter is provided, and can be connected on the one hand to the unit to be attached and on the other hand by means of the attachment elements to at least one attachment device.

Abstract: A monument fitting assembly for installing a monument in an aircraft. The fitting assembly is comprised of a ramp member and a fastening bracket member. The ramp member is attached to a floor of the aircraft. Further, the fastening bracket member is attached to a monument. The fastening bracket member is releasably attached to the ramp member and positions the monument a predetermined height above the floor in a predetermined position within the aircraft and supports the monument in a plurality of load-bearing directions.

Abstract: A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.

Abstract: Adapter devices are provided that, when installed on an aircraft seat track break area, allow for the installation and/or positioning of passenger seats thereat. The devices include a main body having two portions. One end of the portion is integrated to a fork-shaped part 2 which defines a half-opening 3. Close to the end of the other portion there is provided a pair of half-tabs which are symmetrically disposed in relation to one another on each side of the body. Pairs of symmetrically disposed semi-circular tabs are provided on the main body. Threaded pass-through holes are located one of the body portions so as to threadably accommodate retaining discs in the form of screw screws heads provided with screws which are installed in the threaded holes.

Abstract: A loading device 1 for loading and unloading of a cargo hold having at least one conveying system for positioning cargo units in the area of a floor space of the cargo hold, and with at least one guiding element guiding the conveying, and a movement aid in the area of the floor space 11 of the cargo hold 5 enabling rotation and movement of the cargo unit. Sensors detect the presence of a cargo unit in the area of the conveying system without contact the position of a cargo unit on the floor space is determined in at least two spatial dimensions without contact. The sensors make it possible to control rotating movements of the cargo units in the area of the respective conveying systems by a controller.

Abstract: In one embodiment a pivot system is disclosed that has a pivot boss including an engagement extension. A race assembly including a socket for receipt of the engagement extension may be used to couple the pivot boss to the race assembly. At least one conductor may be coupled to at least one of the pivot boss and the race assembly to enable electrical communication between the pivot boss and the race assembly.

Abstract: Non-protruding seat track apparatus and methods are disclosed. In one embodiment, a track includes an elongated support having a support surface and an engagement surface. The support surface is adapted to engage a lower surface of a floor panel, and the engagement surface is adapted to be coupled to a payload assembly. The engagement surface is at least one of flush with and recessed below the lower surface of the floor panel when the support surface is engaged with the lower surface. The engagement surface may have at least one of an engagement slot and an attachment aperture disposed therein.

Abstract: Disclosed is a profile of an end view of a base portion Vertical Take Off And Landing Craft, (VTLC) rotor-blade comprising a widened structure from leading to trailing edges. The profile further comprises straight level planes of air foil that provide the options of transforming the leading edge to the trailing edge. The rotor wing system is housed and duplicated in the craft set within said two wells which are circumnavigated by a corridor from front to aft of the craft. Two rear exits are reinforced by the connection of a triangular structure forming a tail which also affords a comprehensive view of the complete air craft perimeter from the viewpoint of a central top compartment.

Abstract: A cargo rollout stop includes a base, and a guide head pivotally mounted to the base. The guide head is movable between a raised blocking position, and a lowered non-blocking position. A retraction pedal is pivotally mounted to the guide head, and is movable between a first position and a second position relative to the guide head. The retraction pedal permits downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its second position, and blocks downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its it first position.

Abstract: The invention relates to a device for immobilizing an object on an anchor point, a rail or the like, inside a space, especially a cargo hold or passenger compartment of a helicopter. According to the invention, a detachable connecting element is interposed between the anchor point or the rail and the object.

Abstract: A securing device for a loading system in a cargo compartment of an aircraft. The securing device comprises at least one securing catch arranged in the region of a cargo compartment door, a control mechanism and an activation member, in particular a foot pedal.

Abstract: Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture.

Abstract: A terminal (14) for an airport (13) includes multiple servicing levels (82, 102). A ground support service sub-system is coupled to the servicing levels (82, 102) and is configured to mate with a service opening (26) of the aircraft (12). The ground support service sub-system provides services to the aircraft (12) through the service opening (26) and on the servicing levels (82, 102).

Abstract: A system box for accommodating aircraft systems, and for load transmission between an aircraft structure and a crew rest compartment. The system box comprises a first, a second and a third region, wherein the three regions differ from each other. The first region is adapted for attachment of the system box to the primary structure of the aircraft, wherein the second region is adapted for mechanical contact with a crew rest compartment for the aircrew. The mechanical contact in turn is adapted for load transmission between the aircraft structure and the crew rest compartment. Necessary aircraft systems are accommodated in the third region of the system box.

Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container.