Abstract: A aircraft weapons bay acoustic resonance suppression system for reducing undesirable acoustic resonances within an open weapons bay of an aircraft in flight is described. The system includes a rod mounted upon and spaced a distance from an extensible aircraft spoiler. The rod has a hollow core and includes a multiplicity of apertures axially aligned into two groups, placed at the point of fluid separation. A multiplicity of synthetic jets are received within the rod, each jet in fluid communication with a corresponding aperture. The jets combine to form first and second perturbation elements. The perturbation elements are sinusoidally driven out of phase at high frequencies by an actuator. This effectively creates a high frequency forcing of the airstream which is amplified by the airflow, creating a violent shedding. Advantageously, this violent shedding dramatically reduces acoustic resonance within the weapons bay of the aircraft.

Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

Abstract: The present invention relates to self contained, modular integrated deployment and retrieval system for use with an aircraft such as a helicopter. The deployment and retrieval system comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to control the center of gravity of the aircraft and so as to deploy and retrieve the external load.

Abstract: An embodiment of the present invention provides a loading system for loading a stores item onto a release unit attachable to an aircraft structure, the release unit having a release actuation assembly including an actuator arm. The loading system comprises at least one hook pivotably mountable to the release actuation assembly. The hook has a pivot pin passage formed therethrough, a stores engagement portion and an actuation portion. The stores engagement portion is configured for engaging a lifting structure of the stores item. The actuation portion is configured for engagement by the actuator arm of the release actuation assembly to pivot the at least one hook and disengage the stores engagement portion from the lifting structure of the stores item. The loading system further comprises a pivot pin configured for insertion into the pivot pin passage. The pivot pin is removably mountable to the release actuation assembly for pivotably mounting the at least one hook thereto.

Abstract: A method for loading an aircraft (R) with shipping containers (3), the latter being passed on conveyor members (13) into the interior of the aircraft (R) and rotated there in a loading area (8), the position of the shipping container (3) in the loading area (8) is determined and the conveyor members (13) are operated via a control system in accordance with the determined position to rotate the shipping container (3).

Abstract: A radial sonobuoy launch system comprising a clam-shell launch tube and method for launching a sonobuoy. The clam-shell launch tube radially releases a sonobuoy and the clam-shell launch tube is reloaded during flight. The sonobuoys are pneumatically ejected about parallel to the airstream. A pressure boundary structure, having a door and a gate, maintains cabin pressure during reloading and launching. Support arms and drive arms evenly distribute the ejection accelerations from the firing mechanism and guide the trajectory of the sonobuoy during release. A clam-shell launch tube is capable of launching a multitude of differently sized sonobuoys.

Abstract: There is provided a store ejection system, store, and method for mounting a jettisonable store on an aircraft. The system uses a pressurized non-pyrotechnic fluid from a pressure vessel integral to the store and sealed by a releasable seal as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure vessel, a dump valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the dump valve to an open position in response to a control signal to jettison the store. The seal is configured to hermetically seal the pressure vessel before the actuation system is connected to the pressure vessel, and the actuation system is configured to be fluidly connected to the pressure vessel upon release of the releasable seal.

Abstract: There is provided an aircraft which can minimize its radar signature emission. Such aircraft comprises a fuselage having a lower fuselage portion. An internal fuselage cavity is defined within the lower fuselage portion and contains all landing gears and bombs therein. Moreover, a cavity-enclosing door is engaged to the lower fuselage portion. This specific cavity-enclosing door may form a closed position relative to the internal fuselage cavity to enclose all of the landing gears and bombs therein. In this respect, enclosure of all of the landing gears and bombs solely through the cavity-enclosing door may minimize the radar signature emission from the fuselage.

Abstract: In the conventional air cargo transportation system, the transportation of the cargo that is stored inside of the airport terminal building, to the area of the loading/unloading door is normally performed using the package/cargo carts. However, numerous workers were needed to load the cargo and drive the carts, which is very labor intensive and entails high manpower costs. The conventional system is also dangerous as they move along the complex tarmac markings.

Abstract: The present invention relates to a self contained, modular integrated deployment and retrieval system for use with an aircraft such as a helicopter. The deployment and retrieval system comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to control the center of gravity of the aircraft and so as to deploy and retrieve the external load.

Abstract: A system is provided for slowing the speed of a product released into the air from an aircraft. A flexible material wrapped about a product includes a tethered portion thereof that is collapsible against the product prior to release thereof from the aircraft. The tethered portion expands to form an air drag device after the product is released from the aircraft.

Abstract: The specification and drawings describe and show one embodiment of the present invention in the form of an inclined ramp in combination with a lifting device for lifting and lowering articles to and from the tarmac from and to the upper loading area at the top of a service stairway next to a passenger terminal bridge/walkway.

Abstract: A system for deployment of a vacuum-packed inflatable structure includes a primary cylinder with a primary valve that can be opened under a primary applied force for discharging a primary pressurized fluid into the inflatable structure. A first connecting arrangement extends between the primary valve and an inflatable actuator bag. A secondary cylinder has a secondary valve movable under a secondary applied force for discharging a secondary pressurized fluid into the inflatable actuator bag. With this arrangement, application of the secondary force to the secondary valve causes the secondary cylinder to inflate the inflatable actuator bag. This in turn causes the first connecting arrangement to open the primary value with the primary applied force and inflate the inflatable structure.

Abstract: A radial sonobuoy launch system comprising a clam-shell launch tube and method for launching a sonobuoy. The clam-shell launch tube radially releases a sonobuoy and the clam-shell launch tube is reloaded during flight. The sonobuoys are pneumatically ejected about parallel to the airstream. A pressure boundary structure, having a door and a gate, maintains cabin pressure during reloading and launching. Support arms and drive arms evenly distribute the ejection accelerations from the firing mechanism and guide the trajectory of the sonobuoy during release. A clam-shell launch tube is capable of launching a multitude of differently sized sonobuoys.

Abstract: Apparatus for separating aerodynamic objects from an aerodynamic vehicle includes a first element, aerodynamically configured to create nose-down pitching moment, mounted to the object surface, a second element mounted to the first element and projecting into an oncoming airstream such that when enabled, the passing air tears the apparatus from the surface which otherwise supports it. The first element is a body designed to be conformal with the object surface to which it is mounted, and includes a forward end projecting into the oncoming airstream and a rearward end, and is secured to said object surface at the rearward end thereof. A flexible gasket is interposed between the first element and the object surface. The second element comprises a forward end directed toward the oncoming airstream and a rearward end, with the second element being mounted to the first element at the rearward end of the second element.

Abstract: A cargo loader platform having an array of roller assemblies on the deck thereof which are capable of moving a container longitudinally or laterally or rotating it includes several independently driven groups of roller assemblies. The groups include groups along the sides of the platform having drive axes parallel to the loader axis, groups near the center of the platform having a separate drive axes that are perpendicular to the loader axis, and groups down the center of the platform having drive axes parallel to the loader axis. Large diameter, driven cylindrical rollers are mounted on the outer sides of the sides and rear end of the platform to assist in moving cargo onto the deck.

Abstract: The present invention relates to a method and an arrangement for launching counter-measures, such as flares and chaff. According to the invention, the counter-measures are launched in a direction obliquely forwards and upwards relative to the aircraft and a low dynamic pressure is created across the dispenser's launch openings. The arrangement comprises compartments for counter-measures which are provided with openings and are intended for launching the counter-measures in a direction obliquely forwards and upwards relative to the aircraft. The invention increases the possibilities of releasing a target and reduces the noise levels of the sounds which can occur in emptied compartments.

Abstract: A cargo container apparatus and methods of loading cargo. The cargo container apparatus includes a cargo container having first and second opposing side frame portions connected by connecting members and a plurality of liners forming floor and wall portions of the cargo container. The cargo container apparatus also includes a cargo container transporter having a base portion, an elevatable platform, a pair of side support rails, and front and rear ramps. Methods of transporting in a cargo hold are also provided. The methods include expanding a cargo container from a collapsed position, connecting a liner to a lower portion of the expanded container to form a floor, and loading cargo into the expanded cargo container.

Abstract: Improvements in rotorcraft external load operations are disclosed, including a method for transferring a load from an airborne rotorcraft to a structure while providing fall protection for the load and emergency release capabilities for the aircraft. A helicopter is adapted for carrying a load external to the aircraft fuselage which load may be restrained by an FAA approved safety restraint. The load is equipped with a safety harness and lanyard apparatus having first and second lanyards attached thereto. According to the method, a helicopter hovers next to a structure, and safe transfer is accomplished by: (1) attaching the free end of the first lanyard to the helicopter; (2) releasing any auxiliary safety restraint; (3) attaching the free end of the second lanyard to the structure; (4) detaching the first lanyard from the helicopter; and (5) effecting transfer of the load to the structure.

Abstract: A rescue vehicle having a compartment for receiving a movable stretcher having two mushroom-shaped pins located at a front end and a rear end respectively of the stretcher. The compartment has a lateral opening for passage of the stretcher, and which is narrower than the length of the stretcher; a click-on lock unit located at one end of the compartment, such end facing the lateral opening, and for locking a first of the two pins; and a guide unit, which is set back with respect to the lateral opening, is coplanar with the lock unit, and on which a second of the two pins slides during insertion.

Abstract: An aerospace system, which comprises a carrier aircraft, a launch vehicle and a payload.

Abstract: A less-than-200-seat-class airplane includes a fuselage having a horizontal diameter value of a cross-section greater than a vertical diameter value of the cross-section. The cross-section is perpendicular to the longitudinal axis of the fuselage. The fuselage includes a passenger cabin and at least one cargo compartment located below the passenger cabin.

Abstract: A method for refueling and reloading an unmanned aircraft for continuous flight is disclosed herein wherein the unmanned aircraft is maintained and supported by a support aircraft. Both aircraft maintain cargo bays and in-flight operable doors located on the underside of each aircraft for the purposes of docking and exchanging goods. Preferably the goods comprise loadable cartridges and may contain such items as weapons, cargo, or fuel for example. In one embodiment, when both aircraft are in a docked configuration for exchange of goods during flight, the in-flight operable doors open and the support aircraft is capable of loading such cartridges aboard the unmanned aircraft. When necessary the support aircraft may load gear for the purposes of landing the unmanned aircraft. Alternate methods of reloading an unmanned aircraft for continuous flight is disclosed wherein the unmanned aircraft does not have cargo bay doors and the aircraft is supported by a support aircraft.

Abstract: A cargo handling system for cargo compartments utilizes a cargo container which rides along restraining guide rails and on top of rollers situated within and projecting slightly above structural members which are attached to roller possessing cross tracks. The cargo handling system utilizes an omni directional panel just inside the cargo door to facilitate loading, unloading, and rotational alignment of the cargo containers with the guide rails and rollers. Cargo locks situated within the roller channels and the omni directional panel secure the cargo containers in a longitudinal direction of the aircraft fuselage while a side latch within the omni directional panel secures cargo containers vertically, and in a lateral direction. An automatic anti-rollout restraint prevents the cargo container from rolling out of the aircraft while the cargo containers are being loaded or unloaded. Optionally, a power drive unit automatically moves the cargo containers along the rollers.

Abstract: A conformal aircraft bay having a single aperture or gap formed by doors with abutting edge portions being located side-by-side while the doors are in a closed position, the doors are structured to open to access the bay with the abutting edge portions moving apart from each other, and each door having an elastomeric transition closing the gaps between the abutting edge portions when the doors are closed.

Abstract: A loading system for loading a cargo deck in a cargo space of an aircraft with cargo holders is proposed, in which there are provided two pairs of mounting tracks with support rollers and transverse cargo latches, a middle mounting rail for the attachment of transverse cargo latches, and rows of side-mounted transverse cargo latches. The distance between the outer mounting track of each pair of mounting, tracks and the middle mounting rail corresponds to a first, lesser fixation distance of relatively smaller cargo holders (LD2). The distance between the outer mounting track of one pair and the inner mounting track of the opposite pair corresponds to a second, greater transverse fixation distance of relatively larger cargo holders (LD3). As a result it is possible to load a cargo space optimally even if the construction of the aircraft produces constrictions of the cargo space.

Abstract: An air drop container assembly for providing an improved air-drop container for the military and emergency operations. The air drop container assembly includes a container having a top wall, a bottom wall, side walls, and a plurality of compartments disposed therein; and also includes a parachute assembly including a cover being removably disposed upon the top wall of the container and also including a parachute member being removably attached to the container; and further includes a cargo protection assembly being disposed in the container; and also includes a weight assembly also being disposed in the container for providing the container with proper flight orientation as the container is falling through air.

Abstract: To respond to internal threats to the aircraft, an incapacitating aerosol can be released into the cabin of the aircraft. The incapacitating aerosol prevents the hijackers or terrorists from accomplishing their goals. While the hijackers or terrorists are incapacitated, the pilot can land the aircraft at the first opportunity and let trained security forces, such as the police, board the aircraft and deal with the hijackers/terrorists.

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

Abstract: A removable hoisting apparatus for use on an aircraft to hoist cargo and people into the aircraft. The removable hoisting apparatus comprises a base member, a telescoping mast member, a boom member, and a hoist assembly carried by the boom member. The base member is of negligible weight and is adapted for attachment to the floor of the aircraft. The telescoping mast has a bottom portion and a top portion. The bottom portion is releasably connected to the base member, and the top portion is releasably connected to the bottom portion. The top portion extends through an opening in the aircraft. A shoulder member is connected to the top portion, and a boom member is connected to the shoulder member. A rigid link member connects the boom member to the aircraft. The removable hoisting apparatus can be quickly removed from the aircraft by releasing only three quick-release fasteners, leaving only the base member attached to the aircraft.

Abstract: An aircraft fuselage 10 comprising a cargo storage compartment 18, a rear bulkhead 16 at the rear of the compartment for withstanding internal air pressure in the fuselage, a closeable opening 20 in the rear bulkhead 18 through which an elongate item of cargo 25 can be passed, and an opening 26 in the rear of the fuselage 10 through which the said item 25 passes to be despatched from the aircraft with the fuselage 10 de-pressurised.

Abstract: A freight transportation container can accept standardized pallets and is suitable for the transportation by land, sea, or air. The size and construction of the container permits the loading and removal of freight by a conventional fork lift truck, and allows placement of the container in standard-sized trucks and aircraft. Lockdown lips formed on the bottom of the container secure the container to the floors of trucks and aircraft. The freight container also is part of a system for transportation whereby the freight can be loaded, inventoried, locked, and sealed at a customer's premises, and remain under the custody of one entity throughout shipment of the freight to the consignee. An empty freight container can be delivered to a customer's premises on a truck having a cab and removable trailer, so that the container and trailer can remain there for loading, and then later be picked up by the cab and taken to holding areas, other trucks, ships, aircraft, or directly to the consignee.

Abstract: The door (10) of an aircraft incorporates a housing (14) able to receive a slide, in a folded up state. The housing (14) is delimited between a cover (16) facing outwards from the door (10) and intermediate bulkhead (18). The cover (16) is jettisonable outside the aircraft or able to swivel by its lower edge on a threshold of the door, by the use of setting de-setting means. In one embodiment, the housing occupies the greater part of the door surface.

Abstract: A system for an aerial land marking and surveying is disclosed. The system comprises an aircraft carrying a GPS receiver and a land marking device capable of physically marking a point on the ground identified by a computer program. A new method of an aerial land marking and surveying and a land-marking device for carrying out the method are also disclosed.

Abstract: A pallet interface system for supporting a Container Roll in/Out Platform (CROP), flatrack or ISO container within an aircraft, such as a C-17 aircraft. The interface system includes two independent, identical interface pallets which are coupled together by flexible cables. The cables have lengths which enable the two interface pallets to be spaced apart a precise distance so as to be able to support a CROP, flatrack or ISO container. The interface pallets are of small enough dimensions and weight such that same can be manipulated by one or more individuals, thereby obviating the need for a crane to be employed to lift the load onto the pallets before the loading process can begin. Each pallet has a plurality of ISO locking assemblies which allow a CROP, flatrack or ISO container to be locked thereto. Each pallet also has a 463L cargo system edge structure which permits it to be locked to the rails within the C-17 aircraft.

Abstract: A method for providing a communication link from an aircraft (110) to a target (130) is provided. The method includes releasing a first end of a fiber optic cable (120) from an aircraft (110) and then lowering the first end of the fiber optic cable (120) to the target (130). The method also includes connecting the first end of the fiber optic cable (120) to a device at the target (130). The device at the target (130) may then communicate with devices on the aircraft (110).

Abstract: A power drive unit having drive roller elements that transport cargo and a sensor that detects motion of the cargo, e.g., the speed at which the cargo is transported, where the sensor operates substantially independently of the motion of the-drive roller elements. Specifically, the power drive unit comprises a motor, an output shaft driven by a motor, at least one drive roller element fixedly mounted on the output shaft, the drive roller element thereby driven by the motor, a sensor frictionally coupled to the output shaft conditionally permitting relative rotation between the sensor and the output shaft, and a motion detector that detects motion of the sensor. Associated electronics are configured to remove power from the motor driven roller elements where cargo is jammed or parked upon them, thereby increasing the useful lifetimes of the motor and the drive roller elements of the power drive unit.

Abstract: A satellite dispenser adapted to be coupled to a launch vehicle. The dispenser includes a single-piece, integrally formed tubular shell for supporting a plurality of independent satellites thereon. The tubular shell is significantly lighter than multi-piece dispenser shells that require a connecting ring for coupling the post portion and base portion of the shell together. The single piece shell also significantly reduces the cost and simplifies the manufacture of the dispenser shell. The dispenser shell, in certain preferred embodiments, includes a tapered post portion which enables satellites being carried on the upper portion of the post portion to extend further into a fairing disposed over the satellites and dispenser shell during flight, thus making more efficient use of the envelope defined by the interior area of the fairing. A frusto-conical base portion integrally formed with the post portion enables the load supported by the dispenser shell to be evenly distributed throughout the base portion.

Abstract: A cargo container apparatus and methods of loading cargo are provided. The cargo container apparatus includes a cargo container having fist and second opposing side frame portions connected by connecting members and a plurality of liners forming floor and wall portions of the cargo container. The cargo container apparatus also includes a cargo container transporter having a base portion, an elevatable platform, a pair of side support rails, and front and rear ramps. Methods of transporting in a cargo hold are also provided. The methods include expanding a cargo container from a collapsed position, connecting a liner to a lower portion of the expanded container to form a floor, and loading cargo into the expanded cargo container.

Abstract: A method of shipping freight directly from a customer's premises to the premises of the consignee. The method includes transporting to a customer's premises at least one freight container. The freight container includes a base, a roof, a pair of opposed side walls, and a pair of opposed end walls. One of the end walls includes an opening for the loading and removal of freight. The container and the opening are sufficiently large to permit the loading and unloading of freight to and from the container by a conventional fork lift truck. The container has a size of approximately 13 feet long, 8 feet high, and 8 feet wide. The method also includes, at the customer's premises, loading freight into the at least one freight container and securing the freight in the freight container. The method further includes transporting the at least one freight container and its loaded freight, in a secured state, from the customer's premises and to the premises of the consignee of the freight.

Abstract: The present invention relates to an aircraft having a plurality of fuselages for increased payload. More specifically, the aircraft has a central fuselage, and first and second side-saddle fuselages mounted on opposite sides of the central fuselage. The first and second side-saddle fuselages further are provided with a mechanism for opening and each of the side-saddle fuselages define a launch tube such that each launch tube is adapted for transporting and launching a large or oversize missile.

Abstract: Device for loading packages into a cargo hold (3) particularly of an aircraft, wherein loading is effected through a conveyor (4) including a plurality of transport paths (41-43). This conveyor is progressively loaded with packages and moved into the rear area of the cargo hold (3). In order to absorb the longitudinal peak forces possibly occurring particularly during loading and unloading, longitudinal beams (7 and 8) are provided which are mounted on the floor side and support the deflection means (6) against the fixedly mounted drive means (5). Hereby the occurring longitudinal forces may effectively be absorbed within the loading system without the aircraft fuselage (1) being weakened through additional holding means in particular in the side wall area, or even damage being caused to the hull of the aircraft.

Abstract: A loading system for loading a cargo deck in a cargo space of an aircraft with cargo holders is proposed, in which there are provided two pairs of mounting tracks with support rollers and transverse cargo latches, a middle mounting rail for the attachment of transverse cargo latches, and rows of side-mounted transverse cargo latches. The distance between the outer mounting track of each pair of mounting tracks and the middle mounting rail corresponds to a first, lesser fixation distance of relatively smaller cargo holders (LD2). The distance between the outer mounting track of one pair and the inner mounting track of the opposite pair corresponds to a second, greater transverse fixation distance of relatively larger cargo holders (LD3). As a result it is possible to load a cargo space optimally even if the construction of the aircraft produces constrictions of the cargo space.

Abstract: A removable hoisting apparatus for use on an aircraft to hoist cargo and people into the aircraft. The removable hoisting apparatus comprises a base member, a telescoping mast member, a boom member, and a hoist assembly carried by the boom member. The base member is of negligible weight and is adapted for attachment to the floor of the aircraft. The telescoping mast has a bottom portion and a top portion. The bottom portion is releasably connected to the base member, and the top portion is releasably connected to the bottom portion. The top portion extends through an opening in the aircraft. A shoulder member is connected to the top portion, and a boom member is connected to the shoulder member. A rigid link member connects the boom member to the aircraft. The removable hoisting apparatus can be quickly removed from the aircraft by releasing only three quick-release fasteners, leaving only the base member attached to the aircraft.

Abstract: A satellite dispenser adapted to be coupled to a launch vehicle. The dispenser includes a single-piece, integrally formed tubular shell for supporting a plurality of independent satellites thereon. The tubular shell is significantly lighter than multi-piece dispenser shells that require a connecting ring for coupling the post portion and base portion of the shell together. The single piece shell also significantly reduces the cost and simplifies the manufacture of the dispenser shell. The dispenser shell, in certain preferred embodiments, includes a tapered post portion which enables satellites being carried on the upper portion of the post portion to extend further into a fairing disposed over the satellites and dispenser shell during flight, thus making more efficient use of the envelope defined by the interior area of the fairing. A frusto-conical base portion integrally formed with the post portion enables the load supported by the dispenser shell to be evenly distributed throughout the base portion.

Abstract: A basket for supporting equipment between a pair of laterally spaced-apart parallel overhead cables. The basket is provided in the form of a top open container insertable between the overhead cables. A carrying member engageable with a helicopter arm is provided for allowing the basket to be selectively transported between and away from the overhead cables. A pair of wing-like members extend laterally outwardly from opposed side walls of the container for resting on the overhead cables once the basket has been lowered to a suspended position between the overhead cables.

Abstract: A removable hoisting apparatus for use on an aircraft to hoist cargo and people into the aircraft. The removable hoisting apparatus comprises a base member, a telescoping mast member, a boom member, and a hoist assembly carried by the boom member. The base member is of negligible weight and is adapted for attachment to the floor of the aircraft. The telescoping mast has a bottom portion and a top portion. The bottom portion is releasably connected to the base member, and the top portion is releasably connected to the bottom portion. The top portion extends through an opening in the aircraft. A shoulder member is connected to the top portion, and a boom member is connected to the shoulder member. A rigid link member connects the boom member to the aircraft. The removable hoisting apparatus can be quickly removed from the aircraft by releasing only three quick-release fasteners, leaving only the base member attached to the aircraft.

Abstract: A system to quickly convert part of the main deck of an aircraft from a passenger transport configuration to a freight transport configuration. The system includes an arrangement to lock at least one seat pallet flush and rigidly secured to the aircraft deck, for the passenger transport configuration, and an arrangement to anchor a cargo loading assembly to the deck, for the freight transport configuration.

Abstract: A cargo handling system for an aircraft characterized by comprising an elongate endless drive arrangement extending along the intended path of travel of a load unit in use, the endless drive arrangement including a carriage movable along said path and a load unit engaging member on the carriage and movable relative thereto between a load unit engagement position and an inoperative position in response to relative movement between first and second elements of the endless drive arrangement.

Abstract: An arrangement for conveying material to be conveyed along a conveying plane, in particular for freight-loading systems in freight compartments, preferably of aircraft is disclosed. The arrangement provides that driving material to be conveyed along a conveying plane, with which safe, reliable transport of the material to be conveyed is ensured with low wear of the conveying roller under widely varying operating conditions. This is achieved in that, in a drive unit, the conveying roller is connected to a first drive and an associated first activating unit for producing a requisite traction force for moving the material to be conveyed along the conveying plane.