Abstract: A galley unit with a cart lift is provided for elevated storage of a food and beverage cart. The galley unit includes a mounting rack configured for mounting at least one first galley component thereon. The cart lift includes a platform for supporting a second galley component thereon. The platform is movable between a fully lowered, fully extended position and a fully raised, fully retracted position with the second galley component supported thereon. A support pillar is positioned to one side of the mounting rack and is operable to support and manipulate the platform in a fore-and-aft motion between a fully extended position and a fully retracted position, and in an up-and-down motion between a fully lowered position and a fully raised position. The support pillar may include an operator controlled passive lifting system for assisting manipulation of the platform.

Abstract: An airplane has a fuselage shell and a floor structure that includes cross members and floor plates. Rods are used exclusively to connect the fuselage shell to the floor structure.

Abstract: Methods of securing a support beam to a structure such as a cargo roller tray or a passenger cabin is achieved using a shear fitting. The shear fitting has a back plate which fastens to the support beam. The shear fitting additionally has parallel lugs which extend from the back plate and fasten to the structure. Web extenders which extend from the shear fitting perpendicular to the lugs may additionally be used to further fasten the support beam to the structure.

Abstract: A transportation apparatus includes a payload receiving unit, a transportation body, and a compensation system arranged there between providing adjustment of a desired spatial relationship of a payload surface of the compensation unit. The compensation system has at least one of a first compensation unit and a second compensation unit for adjustment of the spatial relationship. The compensation units adjust the spatial relationship in different directions. Thus the compensation system maintains a desired orientation of the payload surface independent of changes of orientation of the transportation surface. Further, the compensation system substantially maintains a common point of gravity of the transportation apparatus including the payload by displacing the center of gravity of the payload receiving unit and the payload substantially opposite to a displacement of a center of gravity of the transportation apparatus.

Abstract: A support system attaches a hoist to the External Stores Support System of an aircraft by using a boom from which a first leg depends and is attached to a forward fitting. A second leg is attached to the boom via a collar and attaches to an aft fitting while a torque arm is pivotally attached to the collar via a support arm, the torque arm also attaches to a tie-down fitting. The legs are attached to their respective fittings using pins and the torque arm is bolted to the tie-down ring fitting. A hoist slip having a horn is attached to an end of the boom.

Abstract: A closet comprises a support rail, a light, a raceway, a rub strip, and a hinge unit. The support rail is capable of providing structural support for the closet and having a plurality of connecting elements. The light has a first set of connecting elements capable of being engaged to the plurality of connecting elements. The raceway has a second set of connecting elements capable of being engaged to the plurality of connecting elements. The rub strip has a third set of connecting elements capable of being engaged to the plurality of connecting elements. The hinge unit has a shape capable of being connected to the support rail.

Abstract: An aircraft stowage bin assembly includes shear fittings configured to route a content load from the bucket of the bin assembly to the airframe in the event of a forward load condition, such as a crash or severe turbulence. When the forward inertial load factor on the stowage bin is greater than about 1 g, the shear fittings create an efficient load path from the bucket to the airframe which bypasses the large metallic or composite endframes required by the designs of many conventional overhead stowage bins. As a result, significant reductions in overall bulk and weight, as well as lower manufacturing costs, can be realized.

Abstract: An overhead luggage bin for an aircraft interior includes a stowage compartment, an upper door movably attached to the stowage compartment and a lower door movably attached to the aircraft interior, the upper door and the lower door being moveable between a closed position and an opened position. A floor of the stowage compartment includes a first portion and a second portion movably attached to the first portion that defines a ramp surface with the lower door in the opened position for improved accessibility. An overhead luggage bin is provided with handles at opposed ends of the stowage compartment and includes one or more non-linear ridgelines and/or increased reflectance on an exterior surface for a more aesthetically pleasing appearance. An overhead luggage bin includes an RFID reader for providing increased RFID functionality. An overhead luggage bin includes a stowage compartment having an integrated handrail.

Abstract: Modular configuration for an aircraft interior floor plan design is provided by an fuselage having starboard and port side attachment rails disposed longitudinally parallel to one another. Each of the starboard and port side attachment rails are comprised of outboard and inboard rails and a center rail positioned therebetween. A plurality of interior fixtures are provided with fixed attachment posts asymmetrically oriented relative to a longitudinal centerline plane of the fixture. Such fixtures can therefore be attached to predetermined pairs of the starboard and port side attachment rails to provide for a desired configuration of the fixtures within the fuselage.

Abstract: To be able to transport and replace in an autonomous manner one of its failing propulsion engines, a plane includes: a fuselage; propulsion engines maintained above the fuselage; maintenance wells traversing the fuselage substantially vertically with respect to the engines in which the engines can be lifted or lowered; a cargo compartment including a floor arranged in the fuselage, where the height, length and width dimensions of the cargo compartment are compatible with the transport of an engine; the cargo compartment and the wells have a common separation wall including an exit whose dimensions allow the passage of an engine; and a lower hatch or ramp for closing the lower opening of the well includes a position in which the upper surface of the ramp is substantially horizontal and substantially in the extension of the floor of the cargo compartment.

Abstract: A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed using conventional means. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

Abstract: An embodiment of the invention, relates to a multifunctional cargo hold system for an aircraft with a cargo hold floor; a retainer rail fitted to the cargo hold floor, suitable for the assembly of means for rolling and/or fixing of loaded elements, wherein the means has a variable assembly with regard to the longitudinal direction of the retainer rail, wherein the cargo hold system has a number of cargo positions, suitable for accommodating elements of the group, including a net for partitioning the cargo hold, a standard container, a palette, a telescopic system, an underfloor catering container, an underfloor rest space, a conveyor of fixed length and a conveyor of variable length, wherein each load position can accommodate at least four of the elements.

Abstract: A storage device for baggage for an aircraft cabin includes a compartment having a lower face and an upper face, an open face allowing access to the compartment for the depositing and removal of baggage inside same and a back, opposite the open face of the compartment. The lower face of the compartment is substantially plane on the side of the open face and rises up near the back. A groove, the concavity of which is positioned toward the upper face of the compartment, is implemented in the joining zone between the raised portion of the lower face and the back.

Abstract: An apparatus for transferring cargo between an upper, passenger deck and a lower, cargo deck of an aircraft. A lift platform raises palletized cargo from the lower deck through an opening formed in the upper deck. The drive mechanism is housed entirely within the lift platform itself. The platform is stabilized by flanking, scissors-action leg assemblies, that nest alongside the platform when stowed. The platform is stowed in the raised position, within the opening formed in the upper deck. Locking assemblies attach the lift platform to the sides of the opening so that the platform becomes a load-bearing structural component of the upper deck when stowed. A recess is formed in the lower deck for receiving the lift platform when lowered. A translating floor assembly having folding floor sections lowers to clear the recess, and then raises to define a floor surface over the opening when the lift platform is not in use.

Abstract: A cargo handling system and method employing a plurality of slide units and tracks. The tracks are mounted in or on a floor of a cargo area of a mobile platform, and also on a ramp of the mobile platform. The slide units slide within the tracks and enable container roll in, roll out platforms (CROPs) and 1077 flatracks to be slidably moved into and out from the cargo area. The slide units are arranged at the four corners of each CROP or 1077 flatrack and can be positively locked to a CROP or 1077 flatrack by a standard ISO twist lock assembly. The slide units eliminate the need for a K-loader and a crane to be present at the site where loading or unloading is to occur. Instead, suitable vehicles such a Heavy Expanded Mobility Tactical Trucks (HEMTTs), which are more readily transported to remote cites, can be used to assist in slidably loading and offloading CROPs and 1077 flatracks.

Abstract: 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, the stowage bin entirely supported by the duct such that the bin is free from direct attachment to an interior wall or supporting structure other than the duct.

Abstract: A system for airborne transport of flammable liquids with an aircraft. A fuel tank and a reservoir, each for storing flammable liquids, are joined to the aircraft. A fuel jettison subsystem is coupled between an interior portion and an exterior of the reservoir to selectably expel fuel from the reservoir to an exterior portion of the aircraft. The fuel jettison subsystem includes a jettison valve opening formed in the reservoir. A lid selectably closes off the opening. A biasing member urges the lid away from the jettison valve opening. A solenoid retains the lid in the jettison valve opening when unactuated and releases the lid when actuated. A jettison linkage is coupled to the solenoid, the jettison linkage being operable to actuate the solenoid. The t lid is urged away from the jettison valve opening by the biasing member when the t solenoid is actuated by the jettison linkage.

Abstract: A safety system for reducing the impact energy of a container for an aircraft includes an aircraft cargo hold with at least one safety wall; an accommodation device; and at least one airbag. The accommodation device can be affixed to the safety wall, wherein the accommodation device is designed to accommodate the at least one airbag. In the case of a movement of the container, the at least one airbag can be activated so that air can be injected into the airbag so that some of the impact energy of the container can be absorbed by the at least one activated airbag, with the remaining forces then being distributed over an area of the at least one safety wall.

Abstract: An ordnance mounting system for a helicopter operatively supports a weaponry support beam above an upwardly projecting floor obstruction in a cabin area of the helicopter, between opposite cabin door openings, with the support beam longitudinally extending transversely through the cabin area, and outer weaponry mounting end portions of the support beam projecting outwardly through the door openings beyond opposite fuselage side walls of the helicopter. The mounting system may be secured to door opening sill structures, or the cabin ceiling or side walls, and permits vertical bending flexure of the installed support beam due to flight and weaponry weight loads on the outer ends of the support beam.

Abstract: Embodiments provide a cargo floor, a system, and a method adapted to be made integral with or complementary of the aircraft fuselage. Cargo floor members may be adapted to be coupled with a flat fuselage bottom inner skin of an aircraft fuselage to serve as the main orthotropic stiffeners to the flat fuselage bottom inner skin such that a portion of the in service loading experienced by the aircraft are shared by a combination of the fuselage and the cargo floor.

Abstract: The invention relates to a device holder for mounting devices in a vehicle. Said device holder comprises at least one external rack and at least one internal rack. The at least one external rack can be mounted on the vehicle structure and has a storage space that is designed to introduce and releasably attach the at least one internal rack. The internal rack has means for forming at least one compartment that has a variable size in order to introduce and mount at least one device. The device holder according to the invention can be particularly well adjusted to the devices that are to be integrated into the vehicle, can optimally utilize the available space, and can be equipped with user-specific devices in standard racks.

Abstract: The invention relates to an aircraft fuselage (12) comprising at least one space arranged in the aircraft fuselage and at least one wall (16). According to the invention, the wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage (12) underneath the space does not comprise burnthrough-resistant insulation. The space can be a cargo compartment of the aircraft or a passenger cabin, while the wall can be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly-fairing). The design, according to the invention, of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: An emergency opening device for an overhead locker with a housing and a lowerable shell includes a connecting element which is connectable to a retention system operatively coupling the housing to the lowerable shell. The emergency opening device also includes a locking device adapted to move from a locked position in which the locking device is coupled with the connecting element to an unlocked position in which the locking device is uncoupled from the connecting element to release the lowerable shell from the retention system.

Abstract: A system and method for a computer program product is provided. The computer program product generates a graphical user interface for controlling a compartment. The graphical user interface comprises at least one compartment graphical indicator, and at least one compartment function button. In another embodiment, a method of managing at least one compartment through an interface supported by a controller is provided. The method includes selecting at least one compartment from the interface, and selecting a function for the compartment from the interface.

Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.

Abstract: The invention relates to a cargo-hold floor for aircraft which is received on a grid structure (1). The grid structure (1) comprises essentially longitudinal members (2) and crossmembers (3). Exchangeably arranged floor plates (80), furthermore roller conveyor apparatuses (50) and lashing points (10) for the fastening of cargo articles, such as pallets, containers or vehicles, are received on the grid structure (1). Furthermore, locking units (98) are provided, which comprise lock elements (100) capable of being folded open and of being folded away. The lashing points (10) are located at the intersection points of the longitudinal members (2) and of the crossmembers (3). The roller conveyor apparatuses (50) and the locking units (98) are always located at the same installation location both in their erected position and in their countersunk drive-over and stowage position.

Abstract: An aircraft gear caddy being removably securely fixable to the bulkhead or other part of a desired aircraft allowing for storage and retrieval during flight of required materials without the need to remove securing devices from the gear caddy.

Abstract: A stowage bin arrangement for fastening a stowage bin for an aircraft, includes a stowage bin unit with a first direction of extension. The stowage bin unit may be fastened to an aircraft structure and be designed such that the stowage bin unit is capable of being telescopically extended along the first direction of extension.

Abstract: A device for introducing forces into a luggage compartment and for transferring and/or distributing the forces and/or stresses in vehicles, particularly in fast traveling vehicles such as aircraft, ground vehicles and watercraft, e.g. express trains, speedboats and the like, has a ceiling-side connecting element arranged between extensions of end-side side walls of the luggage compartment. The device has a simple design and can be economically produced. The invention provides for the introduction of the forces into the luggage compartment via the ceiling-side connecting element, configured, for example, as a strip that distributes forces for stresses.

Abstract: An aircraft comprises a cargo compartment having a cargo-compartment floor, and at least one functional unit, such as a water tank, a waste-water tank, or an electrical equipment rack. The functional unit is disposed on a pallet so that the functional unit can be transported into, and installed in, the cargo compartment. A fixation device attaches the pallet to the cargo-compartment floor.

Abstract: An apparatus for transferring cargo between an upper, passenger deck and a lower, cargo deck of an aircraft. A lift platform raises palletized cargo from the lower deck through an opening formed in the upper deck. The drive mechanism is housed entirely within the lift platform itself. The platform is stabilized by flanking, scissors-action leg assemblies, that nest alongside the platform when stowed. The platform is stowed in the raised position, within the opening formed in the upper deck. Locking assemblies attach the lift platform to the sides of the opening so that the platform becomes a load-bearing structural component of the upper deck when stowed. A recess is formed in the lower deck for receiving the lift platform when lowered. A translating floor assembly having folding floor sections lowers to clear the recess, and then raises to define a floor surface over the opening when the lift platform is not in use.

Abstract: A super-transporter aircraft for transporting at least one element of a secondary aircraft, wherein the structural rigidity of a fuselage of the super-transporter is at least partly imparted by the transported element. The super-transported aircraft can be equipped with a securing device for securing the transported element to the fuselage of the super-transporter aircraft, the securing device adapted to pick up the loads to which the super-transporter aircraft is subjected.

Abstract: A support for aircraft seats and other equipment has a lower support link that sweeps out a lateral arc. The lower support link supports a platform that may have a conventional linear track. The linear track provides fore/aft movement substantially orthogonal to a line tangent to the center of the lateral arc. A pilot link is attached to the platform to form a parallelogram linkage that maintains the equipment platform in a rotationally fixed attitude as the lower support link sweeps out its lateral arc.

Abstract: A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

Abstract: An aircraft for carrying cargo in one or more containers. The aircraft includes a fuselage structure having a plurality of nodes and a plurality of elements connecting the nodes to form a space frame in which to carry cargo. At least some of the nodes are positioned in the space frame based on dimensions of the one or more containers. The fuselage structure is more compact, lighter and less expensive compared to conventional semi-monocoque fuselages.

Abstract: A stowage compartment system for use in an interior area. A support structure is supported from a structural subassembly. At least one compartment is rotatably supported from the support structure. An electrically powered actuator is used to rotate the compartment between open and closed positions. A sensor senses an amperage being drawn by the actuator while the actuator is rotating the compartment. A controller is responsive to the sensor and controls the actuator to interrupt rotational movement of the compartment upon detecting an obstruction.

Abstract: An airborne cargo-carrying apparatus includes support and lower structural frames; a retaining mechanism securing a cargo carrier to the support frame; collapsible nose and tail cones coupled to the frames; flexible side panels coupled to the cones and frames; and a cargo door mounted on the lower structural frame. The support frame includes a top panel. The cones and panels are arranged—with the cones collapsed, side panels folded, and cargo door open—to enable the support frame and the cargo carrier to be secured together with the retaining mechanism engaged. The cones, panels, and cargo door are arranged—with the cones expanded, side panels unfolded, and cargo door closed—to substantially envelop the cargo carrier secured to the support frame within an aerodynamic enclosure.

Abstract: Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals.

Abstract: An object is deployed from an aircraft using gravity extraction of the object with the aid of a small parachute. The object is restrained in the fore and aft directions on either side of the center of gravity by fore and aft loading chains which hold the object to a loading deck. The chains are attached to the object by pear shaped rings mounted to a load plate. The load plate is supported on a lower attachment plate mounted to the object and is attached by a pin to an upper attachment plate also mounted to the object. Pulling the pin causes the load plate to rotate about a hinge formed on the lower attachment plate followed by release of the load plate from the lower attachment plate and the object to be deployed.

Abstract: A system and method for cargo handling is provided. The system includes a transport vehicle including a cargo bay capable of housing a plurality of cargo containers, and a loading dock for coupling to the cargo bay. The system also includes at least one railcar and pylons positioned along a floor of the cargo bay. A predetermined number of pylons are operable to elevate and lower a cargo container within the cargo bay. The present invention also provides a railcar for transporting cargo containers, as well as an apparatus for positioning at least one cargo container within a transport vehicle. The present invention also provides a system for aligning a loading dock and a transport vehicle that includes a mechanism for adjusting the height of the transport vehicle or loading dock, or a plurality of engagement members that are capable of aligning the loading dock and transport vehicle.

Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

Abstract: The present invention provides an aircraft floor of an aircraft consisting of a number of base plates and a number of longitudinal supports and provides an aircraft with a floor of this type. The aircraft floor has transverse joints for partitioning the floor into a plurality of segments transversely to a longitudinal axis of the aircraft, the respective segment consisting of a number of longitudinal support elements, partitioned by the transverse joints, of the longitudinal supports and of a number of base plate elements partitioned by the transverse joints, of the base plates and the segments being coupled together such that they have exclusively a translatory degree of freedom with respect to one another in the direction of the longitudinal axis of the aircraft.

Abstract: An aircraft stowage bin assembly includes shear fittings configured to route a content load from the bucket of the bin assembly to the airframe in the event of a forward load condition, such as a crash or severe turbulence. When the forward inertial load factor on the stowage bin is greater than about 1 g, the shear fittings create an efficient load path from the bucket to the airframe which bypasses the large metallic or composite endframes required by the designs of many conventional overhead stowage bins. As a result, significant reductions in overall bulk and weight, as well as lower manufacturing costs, can be realized.

Abstract: An aircraft for transporting a plurality of cargo containers comprising a forward fairing, an empennage and a spine disposed between the forward fairing and the empennage. The spine is made of a lightweight structure such that the aircraft has insufficient rigidity to withstand bending and tortional loads in flight. A cargo assembly comprising a plurality of modular cargo units is structurally and detachably mounted onto the spine to provide the additional structure to the aircraft required for it to fully withstand the bending and tortional loads of the aircraft in flight. Mounts may be provided to detachably engage the cargo assembly to the spine of the aircraft.

Abstract: An equipment-fastening device EFD to enhance the crash safety of aircraft, for fastening a piece of equipment to a support structure of an airframe, includes a load-limiting release mechanism and a load-peak transformer connected to the release mechanism and having a load-limiting, impact-energy-absorbing deformation element. Load peaks that occur in case of a crash and that stem from equipment fastened to the support structure by means of the equipment-fastening device are first reduced to a residual load peak by the EFD after the release, thereby relieving the stress on the support structure. Only then is any residual load peak that might still remain introduced via a first fastening section of the EFD into the support structure with a time delay vis-à-vis the load peaks that occurred originally.

Abstract: A luggage compartment for aircraft comprises a tilting floor, a flap and a suspension device. The tilting floor is designed for holding carry-on baggage and the like, and may be locked in an initial position and may be tilted to another position for easier loading or unloading. The loading edge height may be substantially lower than the initial height of the closed luggage compartment. For example, an interlocking mechanism may couple the opening and closing of a flap and the tilting of the floor from an initial position to the tilted position, such as a three-position handle that prevents release of the tilting floor until the flap is unlatched.

Abstract: The invention relates to a fixing rail for attaching loading devices, particularly rollers, locking bars or power drive units to the loading deck of an aircraft. This fixing rail comprises a first and a second rail, each rail having a cheek with first attachment devices, to which the loading devices can be fixed, and first floor sections, to which the cheek is attached by a lower edge, each first floor section having second attachment devices, by means of which the floor section can be attached to the loading deck. In this arrangement, the cheeks separated from each other are mountable on the loading devices, so that they are connected to each other by means of the loading devices and the loading deck, following mounting and attaching to the loading deck. In this way, a considerable weight saving is achieved along with increased variability of use of the fixing rail.

Abstract: Cargo hold floors are provided, and comprise panels or similar two-dimensional floor elements for the attachment of roller elements, ball elements, locking bar elements or similar functional elements. Support elements, in particular floor beams, are provided which support the two-dimensional floor elements whereby the floor elements are permanently joined to the support elements to make pre-fabricated floor modules and the floor modules are installable in the aircraft. To make installation work easier, separate load-bearing elements, for supporting the floor modules on and joining the floor modules to a body or a skin of the aircraft, are provided which, before the floor modules are installed in the aircraft, are joinable to the body or skin of the aircraft, and, when the floor modules are installed in the aircraft, are joinable to the support elements. As a result, it is possible in particular cases to make installation significantly easier.

Abstract: A conveyor device is provided for airplane for storing and conveying objects in an arc-shaped shaft. The shaft surrounds an area of a payload space of the airplane. An airplane is also provided with such a conveyor device.

Abstract: A transfer of ordnance units from a first aerial vehicle to a second aerial vehicle performed while both vehicles are airborne. The first aircraft is used as an ordnance storage, ordnance delivery and ordnance supplier platform. The second aircraft has the functionality and capability of delivering the received ordnance to designated targets. The first aircraft includes an ordnance storage apparatus, an ordnance transfer assembly, a computer-based highly accurate ordnance transfer control apparatus, and an ordnance transfer apparatus operating crew. The ordnance transfer assembly establishes temporarily a transfer link between the aircraft and utilizes an ordnance conveyor mechanism for the delivery of the ordnance units. The second aircraft includes a multi-use multi-purpose pylon that receives the transferred ordnance in the proper manner. The aircrafts can be uninhabited.