Abstract: A fuel-efficient method for transporting cargo to a desired location via an aircraft. The method comprises determining the weight of the cargo capable of being transported in a single container, selecting a container having a sufficient weight capacity to support the cargo based on the determined weight of the cargo, and filling the selected container with the cargo. The filled container is loaded onto a location on the aircraft beam relative to the aircraft's CG based on the weight of the filled container to stay within the acceptable CG range for the aircraft. The filled containers having the greater weight are positioned on the beam at or adjacent to the aircraft's CG and the filled containers having lower weight are positioned farther from the aircraft's CG. The containers provide strength and rigidity to the beam to sustain the bending and torsional loads in flight.

Abstract: The pylon of the present invention provides damping of vibrations transferred in both directions between the aircraft and the payload. That is, the pylon of the present invention damps the effects of aircraft vibrations on the payload as well as the effects of payload vibrations on the aircraft. This is accomplished in the present invention by substantially eliminating any rigid connection between the aircraft and the payload under normal operational conditions. Support of the payload is provided by a plurality of resilient suspension elements that are attached to both a base element and a payload interface element. The attachment is such that the payload element is suspended below the base element. Thus configured, the resilient suspension elements dampen the transmission of vibrations between the payload interface element and the base element.

Abstract: A method and apparatus for aligning a swing tail cargo door. An alignment system comprises an alignment ramp, a set of pull-in hook mechanisms, and a set of lock trains. The alignment ramp may be configured for initial alignment between a swing tail cargo door and an aircraft fuselage during closing of the swing tail cargo door. The set of pull-in hook mechanisms may be disposed along an interface between the swing tail cargo door and the aircraft fuselage and may be capable of a final alignment between the swing tail cargo door and the aircraft fuselage during the closing of the swing tail cargo door. The set of lock trains may be disposed along the interface and may be capable of locking a plurality of latch actuators in the latched position.

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract: Conventional support rollers are installed on the floor of an aircraft cargo hold in a mounting profile that comprises side walls, and in an interior space of the mounting profile latch elements can be mounted in order to secure containers, pallets or similar items of freight. To reduce the construction expense, the weight, and the work of assembly, it is proposed that two external rollers be rotatably mounted, outside the interior space of the mounting profile, on an axle that passes through the side walls of the mounting profile.

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: An access platform (208) enables containers (222) to be loaded into a cargo hold (218) of an aircraft (202) from a ground vehicle (220). The platform (208) has two opposite and non-parallel ends (210, 214), between which there is defined a support surface, the platform when viewed in plan having a generally trapezoidal shape. In use, an item (222) of cargo is moved between the cargo hold (218) and the ground vehicle (220) via a door opening, the movement of the item (222) through the door opening being in a direction (213) which when viewed in plan is not parallel to the direction (211) in which the door opening faces. During such movement, the item (222) of cargo is supported by from beneath by the support surface of the platform (208).

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: 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: A watercraft arresting system and method including an entanglement subsystem including at least two arms in a V-configuration. A deployment subsystem deploys the entanglement subsystem so the arms are spread apart in the water in the path of the watercraft to arrest it.

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 new and improved airport system is disclosed herein. Redesigned aircraft dock in a terminal, instead of pulling up to loading bridge and the nose section of the aircraft tilts upwards or to the side for allowing passengers to be removed from the aircraft for deplaning. Cargo and baggage can be loaded using modules that utilize skids, automation, and/or robotics for easy loading and balancing of weight. The airport system will minimize passenger traffic on the airport grounds. The airport system or network includes a secure remote airport facility for servicing one or more airports. The remote airport facility includes a remote tower having a security checkpoint for entering passengers into the secure airport system and then transporting the passengers to the secure airport terminal. Common use aircraft allow a variety of airlines to accommodate passengers on a single flight and reduce fuel consumption and time.

Abstract: The present invention relates to a transport device in cargo spaces in aircrafts, the transport device including a frame structure which, using retaining devices, is provided at the fuselage in the cargo space. The frame structure includes at least one conveyor belt for transport and storage of goods in the cargo space. The retaining devices are provided to retain the frame structure at the fuselage such that it can move in the retaining devices when it is subjected to abnormally high loads.

Abstract: A cargo power drive unit includes a motor and at least one drive roller element coupled to the motor. The power drive unit further includes a light transmitter for emitting light and a light receiver for measuring light. The power drive unit measures an amount of ambient light and then measures an amount of total light after the light transmitter emits light. The power drive unit then determines whether a cargo container is present based on a calculation of reflected light and the measurement of ambient light.

Abstract: A ULD guide includes a base and an arm substantially upwardly extending from the base. A guide member having at least one substantially planar guide surface is pivotally connected to the arm, and is movable between a first guide position and a second guide position.

Abstract: An adjustment device serves for the alignment of supporting parts accommodating in a pivotable manner 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 held with an adjustable movement in a bearing eye of a bearing block, and in that the bearing block has at least two tensioning elements that bear on the bearing insert.

Abstract: A system and method for aiding airdrop computations is described. The system includes a ground system, a data link, and an airborne system. The ground system accumulates substantially real time drop zone GPS and meteorological data, which is transferred to the airborne system via the data link. The airborne system makes adjustments to a release point of the airdrop based on the data received from the ground system. Additionally, the airborne system provides airdrop status to the ground system via the data link.

Abstract: An article carrying device is provided. The device includes a carrier; a plurality of tiers of elevators disposed in the carrier and each of which is movable to a specific height; and an arranging device disposed in the carrier, by which each of a plurality of articles is guided to be arranged on one of tiers of elevators.

Abstract: A launch vehicle is deployed from an aircraft using gravity extraction of the launch vehicle with the aid of a small parachute which assists the extraction and damps the yaw and pitch of the launch vehicle. The launch vehicle is supported on two rows of tires which are rotatably mounted to the aircraft. Gravity and the drag force of the parachute causes the launch vehicle to roll on the tires along the load deck and out of the aircraft. Because the extraction forces are dominated by gravity, the launch vehicle acquires a rotation in the pitch axis as the launch vehicle leaves the aircraft. After the launch vehicle clears the aircraft, the launch vehicle rotates in the pitch plane, and is damped in the pitch plane by the parachute to a pitch attitude which is 70-80° and the vehicle engine is ignited, detaching the drag parachute.

Abstract: A method and system providing a transfer container crane with container code recognition of a container identified by a container code to a container inventory management system is disclosed. The system and method are capable of performing these tasks without the use of non-standard container tagging.

Abstract: Aerial dispersion systems that may be employed to allow rapid and temporary conversion of aircraft for aerial dispersion purposes, such as aerial fire-fighting. The aerial dispersion systems may be implemented using modular components that may be configured for compatibility with conventional cargo loading and unloading systems of modern aircraft, including side-loading cargo systems of wide body passenger and cargo aircraft having high lift capacities. The aerial dispersion systems may be rapidly installed in a large fleet of high capacity aircraft in response to a wildfire or other rapidly-developing emergency such as an oil spill, chemical or biological contamination incident, building or refinery fire, etc. After use, the aircraft of the fleet may be rapidly de-modified and returned to original condition.

Abstract: An integrated operational ground mobility and support system (10) that includes an aircraft (12) having one or more service openings on a side of the aircraft (12). The integrated support system (10) may have an airport interface terminal docking port (14) that has a ground support service sub-system. The docking port (14) mates with the aircraft (12) at the service openings and has multiple service levels. The ground support service sub-system provides services to the aircraft (12) through the service openings and on the service levels. The integrated support system (10) may have in addition to or in replacement of the interface terminal docking port an aircraft loader/unloader. The loader/unloader has ground support service sub-systems and mates with the aircraft (12) at one or more of the service openings. The service sub-systems of the loader/unloader include a passenger ingress/egress system (62) and provide services to the aircraft (12).

Abstract: A device is provided for hoisting a module for mounting into an overhead space, such as the crown of an aircraft fuselage. The device includes a frame that supports the module, and a lifting device that lifts the first frame to properly place the module. The lifting device includes a frame, attachment devices that attach the frame of the lifting device to overhead support frames, and a driving device that moves the frame of the lifting device up the attachment devices. The frame of the lifting device receives the frame that supports the module as the frame of the lifting device is moved by the driving device.

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract: A barrier net (12) across a space defined by the fuselage (6) of an aircraft and a floor (7) of the aircraft comprising a first plurality of parallel lengths (13) orientated in a first direction transverse to a second plurality of parallel lengths (14) orientated in a second direction wherein the lengths (13, 14) have fastening means at each end which provide a means for fastening the net to attachment points on the aircraft fuselage (6), characterised in that neither the first nor the second plurality of lengths (13, 14) is parallel to said floor (7).

Abstract: An aircraft cargo locating system determines the location and weight of aircraft cargo placed in unit loading devices. A wireless tag, such as an Radio Frequency Identification (RFID) tag is affixed to each of the loading devices. The system receives information from the tags, and from the information calculates the location of the loading devices and the weight of the loading devices. The system is able to calculate weight and balance parameters to assist in the loading process.

Abstract: The device (1) for guiding an aircraft at least over an intermediate trajectory between a first flight trajectory for a low-altitude flight and a second flight trajectory which starts at an initial point, and from which trajectory a parachute drop is carried out, comprises means (9) for determining a point of transition which lies on the first flight trajectory which represents the start of the intermediate trajectory, and which corresponds to the point where the aircraft must exit the first flight trajectory so as to reach the initial point under predetermined flight conditions, and means (13A, 13B) which use the point of transition to aid the guidance of the aircraft between the first and second flight trajectories.

Abstract: A rapid deployment system has an inflatable landing tube with an inflatable exit slide coupled to an aircraft. Connectors couple the landing tube to the aircraft. Flexible retarders extend inward from the inner surface of the tube for retarding gravitational descent of cargo and/or personnel from the aircraft. The tube has tubular segments, with ribs and reinforcements, forming a continuous descent tube. A spine along the tube is retractable telescopically allowing for the tube to be retracted within the aircraft. The tube is connected to exterior edges of any exit port of the aircraft. A window coaming adapter is positioned around the exterior edges and a membrane extending between sides of the adapter expands with the landing tube as the landing tube is inflated. The membrane is of multiple layers with expansion cells between adjacent layers for allowing independent expansion of the layers. The entry port has a shield behind the membrane and connected to the aircraft for protecting the membrane.

Abstract: A pivotable pylon for carrying stores, such as ordinance, sensors and pods external to an aircraft includes an elongated strongback coupled against an external surface of the aircraft and generally parallel to the longitudinal axis thereof. An elongated pivoting structure is pivotally coupled to the strongback for parallel pivotal movement relative thereto. A locking mechanism locks the pivoting structure in a selected one of a plurality of angular positions relative to the strongback. At least one stores rack is coupled to the pivoting structure for receiving and coupling at least one stores item to the pivoting structure. An aerodynamic fairing may be disposed on the pylon to decrease drag. The pylon can be mounted on either side of the aircraft and in any one of a plurality of longitudinal stations, and enables the aircraft to carry stores that are too large for its equipment bays, and to carry an optimal load of stores.

Abstract: Aircraft loading apparatus includes a frame removably attachable to an aircraft (e.g. a helicopter). The frame is constructed for assembly and disassembly in a transitional position and includes a pair of raising and lowering mechanisms. The mechanisms include a pair of belts with free ends attachable to form a sling and connected for simultaneous extension or retraction of equal lengths of each belt. In operation, the frame is attached to the aircraft adjacent an area at which an article (e.g. an auxiliary fuel tank) is to be connected. The article is positioned under the frame and the belts are extended to form a sling around the article. The mechanisms are activated to simultaneously retract equal lengths of each belt to raise the article into a connecting position, the article is connected, and the frame is disassembled into a removable configuration and removed from the aircraft.

Abstract: A jet aircraft with integrated, rotary sonobuoy launch system has storage racks for a number of sonobuoys in sonobuoy launch containers; and one or more launcher units in its cabin. Each launcher unit has a pressure shell with a door allowing loading of sonobuoys in sonobuoy launch containers from the storage racks. With the door closed, the inside of the shell can be depressurized for launching a sonobuoy by opening a gate valve that connects the interior of the shell to the exterior of the aircraft. With the gate valve closed, the shell can pressurized so that the door can be opened and sonobuoys reloaded. A control system can be used to rotate a rotary launcher inside each pressure shell so that a selected sonobuoy is moved to a launch position above the gate valve and a launch tube, and a pneumatic system can be used to launch the sonobuoy.

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract: The invention provides a method for the aerial transfer of munitions from a rearming aircraft to the weapons pylon of the recipient combat aircraft. The invention also provides for the selection of munitions from a database of munitions and aircraft types in response to an Air Tasking Order. The invention allows a variety of combat aircraft to be adapted to aerial rearmament. The invention also allows the release of precision guided munitions directly from a rearming aircraft so that orbiting combat aircraft can guide these munitions to the target by remote control.

Abstract: Processes for positioning, securing, and repositioning payload assemblies onto floor assemblies are disclosed. In one embodiment, a method includes forming a support structure having a plurality of elongated engagement members, each engagement member including an engagement surface adapted to support a load; forming an adaptable payload assembly that includes a payload member and at least one payload support coupled to the payload member, the payload support being adapted to transmit loads from the payload member to at least one engagement member, the payload support being moveable with the payload member relative to the support structure; and removeably coupling the payload support to at least one of the engagement surfaces of the engagement members. In an alternate embodiment, the engagement surfaces are at least one of approximately flush with and recessed below a lower surface of a panel supported by the support structure.

Abstract: Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

Abstract: A static discharge cable is attachable to a rescue hook or other component being lowered by an aircraft. The cable has a first fitting attachable to the hook or other component, a second fitting attached to the first fitting, and a conductive cable attached to the second fitting. The first and second fitting are attached using a shear pin. Attached to the other end of the cable is a light holder.

Abstract: An aircraft cargo loader includes a first generally horizontal platform structure adjustable in height between ground level and a first elevated position. The loader includes a second generally horizontal platform structure positioned adjacent to the first generally horizontal platform structure and adjustable in height relative to the first platform structure. A third generally horizontal platform structure is positioned adjacent to the second generally horizontal platform structure and is adjustable in height relative to the first and second generally horizontal platform structures. The aircraft cargo loader may include additional platform structures and one or more may be carried by a vehicle.

Abstract: A vehicle including a fuselage, at least one lift-producing propeller carried by the fuselage on each side of its transverse axis a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with the longitudinal axis, and a pair of payload bays formed in the fuselage between the lift-producing propellers and on opposite sides of the pilot's compartment. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions.

Abstract: An automated airline baggage transportation system includes a tug connectable to an airplane and a plurality of guide rails for automatically directing an airplane to a gate terminal. The system further includes a plurality of flexible and elongated conveyor tubes selectively positionable between an airplane and an airport terminal, and a plurality of baggage loaders with adjustable arm loaders for guiding baggage between the plurality of conveyor tubes and an airplane. The plurality of adjustable arm loaders are connected to a plurality of shelves disposed in an airplane bin for assisting to transport the baggage between the shelves and the conveyor tubes. An adjustable gate pier including a plurality of baggage chutes is connected to a gate terminal and is selectively extendable outwardly and away from a gate terminal so that baggage can be presorted for transportation towards or away from an airplane via the plurality of conveyor tubes.

Abstract: A method of loading a ULD into a cargo compartment of an aircraft through a loading door opening of the cargo compartment, which method requires turning of the ULD and comprises the steps of: loading the ULD into the compartment to a first position, rotating the ULD about a first pivot axis to a second position wherein the second position includes a portion of the ULD protruding outside the compartment through the loading door opening, and rotating the ULD about a second pivot axis to a third position wholly within the compartment. The invention further resides in a method of unloading, an apparatus for loading and unloading, and a control system for controlling loading.

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract: Roller drive units are used for conveying objects, in particular cargo containers, on a roller conveyor track of an aircraft. They comprise a drive motor, a planetary gear with an input connected to the drive motor and with a first as well as a second gear output. A drive roller is connected to the first gear output to propel the object and a lifting apparatus is connected to the second gear output to lift the drive roller out of a retracted resting position, in which the drive roller does not contact the object, into a raised operating position in which the drive roller can engaged with the object. A first brake is provided to slow down the drive roller and a second brake is provided to keep the lifting apparatus in position. To improve the traction characteristics and in particular to improve the force with which the drive roller can press against the object to be conveyed, the first and second brakes are constructed so as to be controllable.

Abstract: A power drive unit (PDU) for cargo handling systems comprising a frame arranged to be mounted in use for raising and lowering movement relative to a supporting structure, a drive motor carried by the frame and having an output shaft, a drive roller assembly carried by said frame for engagement in use with a unit load device (ULD) or the like to be moved by the PDU, a first gear train transmitting drive from said motor output shaft to a drive roller of said drive roller assembly, a rotatable lifting cam assembly carried by said frame and driven in use relative to said frame to lift and lower the frame on said mounting, a second gear train for transmitting drive from said motor output shaft to said lifting cam assembly to operate said lifting cam assembly, clutch means operable to connect and disconnect said motor output shaft to and from said second gear train, a torque limiting device limiting the torque transmitted through said clutch, when said clutch is engaged, to said lifting cam assembly, and a brake me

Abstract: A single transportation platform system capable of interfacing with standardized ISO containers, PLS truck-and-trailer systems, HSVs Fast Sealift Ships, and cargo aircraft's 463L rail and pallet locking systems. The system can be handled by a LHS equipped vehicle as a joined platform or separated into individual pallets and handled like a 463L pallet. The platform provides a pallet system that eliminates the need for a married pallet system to be used in the process of loading and supporting loads normally transported on standard CROPs when being transported on a cargo aircraft. The platform can be positioned directly on the roller assembly of a loading ramp of a cargo aircraft, such as a C-17 by a LHS equipped vehicle, so as to facilitate loading and unloading from the aircraft without the need for large cranes or K-loaders. The platform also permits combat offloads to be performed.

Abstract: The capture of payloads carried by a descending parafoil is facilitated by the use of a trailing line from the parafoil that is snagged by a hook on a recovery line from a helicopter. The trailing line can be more easily snagged by the use of a drogue at its end to facilitate the extension of the trailing line. The trailing line can take the form of a loop extending from the parafoil canopy. The trailing line can actuate a slider to collapse the parafoil's suspension lines and canopy for easier handling by the capturing helicopter. Cutters can be installed on the lines holding the load to cut those lines when the recovery line pulls to hoist the load, thus separating the parafoil from the load as the load is lifted by the helicopter.

Abstract: A single transportation platform system capable of interfacing with standardized ISO containers, PLS truck-and-trailer systems, HSVs Fast Sealift Ships, and cargo aircraft's 463L rail and pallet locking systems. The system can be handled by a LHS equipped vehicle as a joined platform or separated into individual pallets and handled like a 463L pallet. The platform provides a pallet system that eliminates the need for a married pallet system to be used in the process of loading and supporting loads normally transported on standard CROPs when being transported on a cargo aircraft. The platform can be positioned directly on the roller assembly of a loading ramp of a cargo aircraft, such as a C-17 by a LHS equipped vehicle, so as to facilitate loading and unloading from the aircraft without the need for large cranes or K-loaders. The platform also permits combat offloads to be performed.

Abstract: The invention relates to the aerospace engineering and can be used for jettisoning boost rockets from an aircraft. The inventive device comprises a landing container (3) with an open end (4) provided with a high-pressure source (5). The freight to be jettisoned (2) is arranged in two sections inside the container (3) on mounting elements (10), one of which is embodied in the form of a calibrated support (9). The values of maximum efforts and acceptable lateral movements (13) of the supports (9) are chosen in such a way that a minimum positive allowance (12) between the container (3) and the freight (2) is provided. The supports (9) are provided with dampers. The aim of the invention is to reduce a transverse load affecting the freight to be jettisoned landing.

Abstract: The aircraft with multi-level cabins functioning as a cargo cabin or passenger cabin comprises a first cabin provided with a cargo hatchway which is opened and closed by a cargo door on a fuselage, the cargo door facing towards the cargo cabin; a second cabin which lacks the cargo hatchway, the second cabin being positioned directly above or under the first cabin; and an elevator to convey a cargo item, moved into the first cabin through the cargo hatchway, to the second cabin, and to convey back the conveyed cargo item from the second cabin to the first cabin, thereby the cargo item is moved between the exterior of the aircraft and the second cabin.

Abstract: A payload deployment system is described that includes an external shell or tube within which an internal cargo unit is placed. The internal cargo unit encapsulates one or more payloads and seals the external shell or tube. Payloads are deployed in a two step process. The first step involves ejecting the internal cargo unit from the external shell or tube. The second step involves separating the internal cargo unit into two or more pieces in a controlled and, possibly, time-sequenced manner so as to deploy one or more payloads housed within the internal cargo unit. The internal cargo unit is ejected from the external shell or tube by a first separation device and the internal cargo unit is separated by a second separation device. Illustrative separation devices include, but are not limited to, pyrotechnic and clamp-and-spring devices.

Abstract: A method of ejecting or jettisoning stores from an aircraft is disclosed that pertains essentially to the over-pressurizing of an on-board gas storage system such that the pressure of the gas stored therein remains at or above the proper pneumatic actuation pressure during all foreseeable temperature ranges. When a control signal to release a store is provided, the pressure of the gas is reduced to be within the desired pneumatic actuation pressure and the gas is then used to release the store. The present invention eliminates many of the concerns associated with prior art ejection systems by providing a method of supplying proper pneumatic actuating pressures during store release without the need for on-board compressors or heating elements.