Abstract: Aircraft passageway storage units are disclosed herein. An example apparatus includes a storage assembly to be supported on a floor of an interior of a fuselage of an aircraft. The storage assembly has a corner to be adjacent a passageway of the interior of the fuselage, and the passageway is to extend around the corner. The example apparatus also includes a door coupled to the storage assembly. The door extends from a first side of the storage assembly to a second side of the storage assembly and defines a portion of the corner. The door is to cover an opening of a compartment of the storage assembly when the door is in a closed position, and the opening is to extend from the first side to the second side.

Abstract: An aircraft floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember.

Abstract: An apparatus for affixing an object to a rail includes, but is not limited to at least one base body, at least one locking body and at least one operating element. The locking body is held so as to be movable relative to the base body and is connected to the operating element by way of at least one bearing. The operating element is arranged so as to be rotatable in the base body, includes, but is not limited to a cam that acts on the base body, and when rotated moves the locking body towards the base body. In this way apparatus is created which makes possible the manual affixing and undoing, without the need for tools, of an object on and from a rail, for example, if needed, in order to reposition displaceable monuments in a cabin of an aircraft.

Abstract: A fastener device (10) provided with attachment means (20) for attaching an external load (5) and with fastener means (30) provided with a support beam (40) and with anchor means (50) for anchoring said support beam (40). A first mechanical coupling (60) connects said support beam (40) to the anchor means (50) so as to enable the support beam (40) to pivot about a first pivot axis (AX1). In addition, coupling means (70) are hinged to the support beam (40) so as to make pivoting possible about a second pivot axis (AX2), the attachment means (20) being hinged to the coupling means (70) to make pivoting possible about a third pivot axis (AX3). This fastener device (10) includes automatic folding means (100).

Abstract: A fastening device is provided for an aircraft interior equipment component, with at least one suspension point which is formed to transmit forces to a holding structure in at least one direction. In order to install the aircraft interior equipment components quickly and without tools, each suspension point is formed by a rotatable sliding block and a groove, wherein the groove has a transverse dimension as well as a first open end and a second end which leads into a circular recess. The sliding block also has a transverse dimension which is smaller than or equal to the transverse dimension of the groove and a longitudinal dimension which is greater than the transverse dimension of the groove, so that the sliding block can be positively locked by a rotation thereof in the circular recess.

Abstract: A test apparatus for avionic sensors including a helicopter, an avionic sensor test pod equipped with at least one avionic sensor and a cable suspension system connecting the test pod to the helicopter.

Abstract: An assembly that includes a first part composed of a fibrous structure that includes fibers and a cured resin matrix. The fibrous structure has at least one surface and a layer that is located on the surface. The layer includes a discontinuous fiber composite that is composed of randomly oriented short fibers and a cured resin matrix wherein the layer has been machined to provide a machined surface. The assembly also includes a second part that is attached to the first part. The second part includes at least one surface that fits against the machined surface on the first part.

Abstract: An aircraft cargo compartment container crane system including an aircraft having an upper passenger compartment and at least one lower cargo compartment, wherein the passenger compartment and the cargo compartment are separated by a floor and a crane assembly connected to a structural element of the cargo compartment beneath the floor, wherein the crane assembly is configured to lift and move a cargo container within the cargo compartment along a longitudinal axis of the aircraft.

Abstract: A method and apparatus are provided for at least partially environmentally isolating a volume, such as by environmentally isolating the cargo compartment from the passenger compartment of an aircraft. In the context of an apparatus, a barrier curtain is provided that partially defines the volume. The apparatus also includes a cable extending along one or more walls that partially define the volume. The barrier curtain is supported by the cable. The apparatus may also include a cable release mechanism attached to a respective wall. The cable is carried by the cable release mechanism and the cable release mechanism is configured to fail at a predetermined load, thereby permitting the barrier curtain to drop in response to a decompression event.

Abstract: An overhead equipment stowage pod comprises a base having a structural material surrounding a central opening. The central opening is open on top and bottom, and the base is fastened to a support structure proximate a ceiling. A replaceable stowage bin is at least partially inserted through the base into the ceiling, and a closeable door is suspended below the stowage bin.

Abstract: The present invention relates to a removable support (10) for optional equipment (6) on an aircraft (1). The support (10) comprises an elongate beam (20) fitted with at least one attachment point for a piece of equipment and extending from a first end portion (21) to a second end portion (22), and the support (10) is provided with first fastener means (30) provided with a first fastener arm (31) connected to a first link arm (32) that is releasably fastened to the first end portion (21), and with second fastener means (40) provided with a second fastener arm (41) connected to a second link arm (42) that is releasably fastened to the second end portion (22), a first support rod (34) also connecting the first fastener arm (31) to the first link arm (32), and a second support rod (44) also connecting the second fastener arm (41) to the second link arm (42).

Abstract: Gimbal system, including method and apparatus, for mounting a gimbal apparatus to a support platform with a mount assembly. The mount assembly may include first and second bar assemblies that are rotationally coupled to each other by a pair of gears.

Abstract: A multifunctional module is provided for a passenger services conduit in an aircraft. The multifunctional module includes, but is not limited to a first interface and at least one utility unit for providing a passenger with services. The first interface is for connecting the utility unit to the passenger utility conduit, the interface, for example, being designed as a mechanical interface.

Abstract: A multifunctional cargo hold system for an aircraft includes a cargo hold floor; a retainer rail fitted to the cargo hold floor, suitable for the assembly of units for rolling and/or fixing of loaded elements. The units have a variable assembly with regard to the longitudinal direction of the retainer rail. 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 swing down mount system for mounting a camera gimbal or other viewing/recording device to a helicopter is disclosed. The system comprises a frame, an axle mounted on the frame, an arm attached to the axle, a camera gimbal or other device mounted on the arm, and one or more counterweights. During landing and takeoff, the system is positioned substantially horizontally below the fuselage of the helicopter so that the helicopter can touch down on the ground without interference from the system. In the air, the mount is able to position the camera gimbal below the skids or wheels of the helicopter so that the camera gimbal has a 360-degree field of view that is unobstructed by the structure of the helicopter. When the camera gimbal is moved from one position to another, the counterweights swing in opposition such that the lateral center of gravity remains substantially unchanged or within acceptable limits.

Abstract: A fastener system (10) having attachment means (15) for attaching an external load to a rotorcraft, said fastener system (10) having a support beam (20) for attaching the attachment means (15) to a rotorcraft, said support beam (20) having a horizontal core (25) and two lateral section members (30) extending in elevation from said horizontal core (25), said fastener system (10) having a support member (50) in a central space (100) between said lateral section members (30) to carry attachment means (15), said support member (50) being connected to each lateral section member (30). Each lateral section member (30) includes a web (31) in elevation connected to the horizontal core (25), each web (31) presenting an obtuse angle (?) relative to said horizontal core (25) in said central space (100), each lateral section member (30) being a sloping section member capable of moving closer to said horizontal core (25) under the effect of vertical forces.

Abstract: A fastener device (10) for fastening a load to a rail (4) that is provided with a slideway (4?) defined by a bottom wall (5), two side walls (6), and a top wall (7) including a succession of wide slots (8) and of narrow slots (9), said fastener device (10) comprising a base (20) and two shoes (30) suitable for being inserted in said wide slots (8) and for co-operating with the top wall (7) in a narrow slot (9) by shape interference. The device further comprises first and second slides (31, 32), each including one of said two shoes (30), spacer means (40) for spacing apart said first and second slides (31, 32), detector means (50) for detecting a rail (4?), approach means (60) for causing said first and second slides (31, 32) to approach each other, and blocking means (70) for longitudinally blocking said base (20).

Abstract: The system and apparatus of the present invention is generally comprised of a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly which are affixed to the Air Deployment System (ADS) rails, cargo tie down “D” rings, seat belt restraint ring bolt sockets, and litter bar of a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

Abstract: An integration method and module aims at simplifying the electrical connections between equipment and an electrical power center to be supplied electricity, while enabling a good accessibility of each piece of equipment for easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to connect the equipment in a direct extension of the electrical power center. According to one embodiment, an integration module includes a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power center. Cells, which define a constant cross section and an adjustable width enabled by movable intermediary walls, extend perpendicularly to the main longitudinal axis. Such cells are adapted to receive formatted electrical equipment.

Abstract: Surface-area safety means (10) comprising a barrier net (20) and at least one fastener means (30), each fastener means (30) having a fastener strap (40) fastened to a segment (25) of said barrier net (20) and co-operating with a fastener member (50) suitable for fastening said fastener strap (40) to said structure (2). The fastener means (30) also include a tensioning strap (60) fastened thereto, said tensioning strap (60) including at least two tensioning eyelets (61), said fastener strap (40) having a securing system (200) for securing it to a tensioning eyelet (61) and securing the fastener strap (40) to the tensioning strap (60) by passing through a particular tensioning eyelet in order to tension said barrier net (20) to the tension corresponding to the particular tensioning eyelet.

Abstract: An aircraft area comprises a door, a door aisle and a main aisle. A storage cabinet for emergency equipment objects is disposed adjacent to the door aisle and/or the main aisle, and has an access point that is reachable from the door aisle and/or the main aisle.

Abstract: A cart for carrying a lineman along power line conductors includes a basket, vertical supports, a frame overhanging the basket, the frame mounting rollers which engage the conductors. The frame, vertical supports and basket define a generally C-shaped opening between the frame and the basket through which the conductors pass into vertical alignment with the rollers on the frame. The basket includes a wall remote from the opening which extends upwardly and away from the opening to provide a protected area for the lineman, the vertical supports being positioned between the opening and the area for protecting the lineman from conductors passing through the opening. The cart includes a safety cable affixed to the basket at the opening and removably attachable to the frame at the opening to provide a structural connection between the basket and the frame for strengthening the cart structure during cart movement.

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: A movable storage compartment for a passenger cabin comprises a housing and fixing structures on the side walls of the housing, the housing being open on one side and being able to be moved back and forth between an open and a closed position, that is to say being able to be opened and closed. The fixing structures are formed in such a way that during a movement from the open position to the closed position the housing can be moved first predominantly rotationally and then predominantly translationally upwards.

Abstract: Lightweight blast mitigating composite panels (10) include a first glass composite shell (14; 152), an intermediate, preferably honeycomb layer (56; 156), a reinforcing layer (60; 160), an ultra high molecular weight polyethylene fiber (UHMWPE) layer (64; 164) and a second glass composite shell (15; 168) adhered together with fire resistant adhesive layers (54; 58, 63, 66; 154, 158, 163, 166). The UHMWPE layer (64; 164) includes top and bottom coatings (70, 71) of fire resistant thermoset plastic preferably in the form of a paste. The panels (10) have use in a wide range of applications including in a blast mitigating overhead storage bin (100). The storage bin (100) includes a main body portion (133) defining a storage area formed from composite unarmored and armored panel segments (137, 138; 128-132).

Abstract: The invention provides an aircraft with a ventral fairing able to store equipment and systems in lateral zones. The ventral fairing (20) comprises a first zone of length L1 along the X-axis, where the area of the cross-section perpendicular to the X-axis increases in the direction of the air flow and a second zone of length L2, where the area of the cross-section perpendicular to the X-axis decreases in the direction of the air flow, being L1>L2 and being placed the rear end of said first zone behind the intersection of the trailing edge of the wing (15) with the fuselage (13).

Abstract: Disclosed herein is an asymmetric luggage stowage bin arrangement, with a pair of compartments attached to a single bin housing. The compartments being unequal in length, to optimize the storage capacity of the bin housing relative to the most common luggage dimensions on the market. In one form, the asymmetric luggage stowage bin arrangement is used as a retrofit to replace shelf-style luggage stowage compartments common to older style aircraft.

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

Abstract: A piece of furniture for an aircraft, including a plurality of carriages a first section forming an interface of use for a user with which at least one carriage may be taken and/or deposited in the piece of furniture and a second section allowing the said carriages to be circulated along at least first and second main directions substantially perpendicular to each other, at least in a plane of the aircraft for storing and/or delivering to the user at least one carriage, the first section and/or the second section including an arrangement for distributing at least one carriage from the second section towards the first section and vice versa.

Abstract: A system for retractable equipment is proposed that has movable protection flaps and in which a flap drive device serves to drive the flaps in optimized movement, while providing mechanical coupling between the flaps and the retractable equipment in such a manner that a common motor member can be used for driving both the equipment and the flaps. The drive device includes a cam secured to a frame of the system and a cam follower mechanically coupled to the retractable equipment and to a flap drive member. The path followed by the retractable equipment can thus also be optimized.

Abstract: A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

Abstract: An overhead luggage compartment for a vehicle cabin is provided. In the compartment, a ledge provided with an electrical component is pivotably held in a housing half-shell about a pivot axis. The pivot axis extends through two axles connecting the ledge to the housing half-shell. For connecting the electrical component to a cable, one of the axles has a through-hole extending in the axial direction, through which the cable is guided for connecting the component.

Abstract: The invention relates to a device for developing an aircraft hold located under the floor of the passenger cabin and the cockpit and including a so-called commercial area in which freight can be transported and a technical area including technical equipment and located at the front of the commercial area an at least partially under the cockpit, wherein said device includes: at least one compartment sealed relative to the hold located at the front of said commercial area and at the back of a portion at least of the technical area; a staircase connecting each compartment to a portion of the intermediate floor between the passenger cabin and the cockpit; and a sealed corridor extending from said staircase to each of said sealed compartments.

Abstract: Aircraft having multiple seating configurations and associated systems and methods are disclosed. An aircraft in accordance with one embodiment, for example, can include a fuselage having a generally circular cross-sectional shape and one or more passenger cabin portions. The individual cabin portions can include a floor connected to the fuselage and a plurality of passenger seats attached to the floor. The passenger seats are in a configuration selected from a first twin aisle seat-row arrangement and a second, single aisle seat-row arrangement. Each of the first and second seat-row arrangements is implementable in the fuselage. Further, the seats in either the first seat-row arrangement or the second seat-row arrangement have between a three abreast and a six abreast seating configuration.

Abstract: A cryogenic tank includes a shell having an interior side, an exterior side, and an internal volume that is bounded by the interior side. The shell has a shape that includes at least two elongated lobes that are defined by partial cylinders that intersect each other. The partial cylinders extend lengths along central longitudinal axes that are offset from each other. The lobes include opposite domes that extend at opposite ends of the length of the corresponding partial cylinder. The cryogenic tank includes an internal reinforcement frame having a web of elongate frame members extending within the internal volume. The frame members extend along the interior side of the shell such that lengths of the frame members extend along paths that follow the profile of the interior side of the shell. The internal reinforcement frame is configured to distribute loads exerted on the shell along at least three different directions.

Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

Abstract: Sensor pod attachment assemblies are provided for attaching a sensor pod containing airborne sensor equipment to an aircraft fuselage. The sensor pod assemblies may include fore and aft pairs of attachment pylon assemblies each having a lower end attached to the aircraft fuselage and an upper end attached to the sensor pod. The fore pair of attachment pylon assemblies can include port and starboard pylon structures, and a cross-support base connected to upper ends of the port and starboard pylon structures. The aft pair of attachment pylon assemblies may include a lengthwise adjustable spar assembly.

Abstract: A cargo storage and handling system for aircraft. A rack assembly mounts in an upper portion of the fuselage to form a cargo area in the upper lobe thereof. The rack includes a series of frames that are suspended from pre-existing attachment points for luggage bins. Cargo rails mounted on the frames support containers for movement through the upper lobe cargo area. Cargo may be raised to the upper lobe cargo area from the main deck of the aircraft using a lift apparatus. The lift apparatus includes a platform that is raised/lowered by a lift mechanism, the lift mechanism being mounted to/or enclosed within a barrier between the cargo and personnel areas of the aircraft, such as a 9G Barrier. A cover apparatus closes a cargo hole in the main deck of the aircraft for personnel safety.

Abstract: A method and apparatus for converting aircraft from civilian cargo to CRAF use includes a pallet guide attached to the cargo deck of the aircraft. The pallet guide includes a pair of L-shaped structural channel members that are arranged back-to-back and staggered longitudinally along the length of the aircraft cargo deck. The L-shaped guide members are staggered back-to-back to enable military 463 L pallets to be guided along both the port and starboard sides of the pallet guide with one row of pallets loaded transverse to the centerline and one row of pallets loaded parallel to the centerline. The pallet guide includes a third guide member comprising a substantially T-shaped body displaced laterally with respect to the L-shaped guide members. For loading and unloading standard commercial pallets, the L-shaped guide members are rotated into a retracted position below the deck height of the cargo deck.

Abstract: A control system is provided that adopts a communication network using wireless visible light and IR light communications in a galley of an aircraft which is subjected to limitations of aviation regulations regarding wired communications. Insert equipments each having a visible light receiving element and an IR emitting element are disposed in a galley of an aircraft, and a galley controller is disposed within the galley or a circumference area thereof having a visible light emitting panel, an IR receiving element and a display/control panel for controlling the insert equipments. A mutual communication function between the galley controller and the insert equipments and a remote control function for controlling the insert equipments from the galley controller are realized via transmission and reception of visible light communication data and IR communication data.

Abstract: A container assembly and aircraft fuselage for air transport of freight. The container assembly includes a spacer layer formed of malleable material. The spacer layer is positioned between and in contact with a bottom plate of the container and the floor of an aircraft. The aircraft fuselage for the freight transport is equipped with a floor adapted to receive and bear a load. A spacer layer integral with the floor is positioned between the floor and the load. The spacer layer is formed of a malleable material.

Abstract: Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever (58, 95).

Abstract: An electrically activated latch for aircraft stowage bins includes an overhead stowage bin module having a stationary support structure and a movable stowage bin portion. An electrically operated stowage bin latch mechanism latches the movable stowage bin portion in a closed position and unlatches the movable stowage bin portion to an open position. An electrically operated stowage bin activation switch operates the stowage bin latch mechanism, allowing the aircraft stowage bins to be locked by independently controlling the overhead stowage bins through the aircraft cabin management system, or by control of the latch by the stowage bin activation switch.

Abstract: Embodiments of the present invention provide systems and methods for using aircraft lavatories as storage when the aircraft is on the ground and during taxi, take-off, and landing, but to also allow the lavatories to be open for use during other aircraft flight times. This is accomplished by providing a slidable unit that is contained within the interior space of the aircraft lavatory in a storage position and that is extended out of the aircraft lavatory space in a lavatory use position.

Abstract: Disclosed herein is an asymmetric luggage stowage bin arrangement, with a pair of buckets attached to a single bin housing. The buckets being unequal in length, to optimize the storage capacity of the bin housing relative to the most common luggage dimensions on the market. In one form, the asymmetric luggage stowage bin arrangement is used as a retrofit to replace shelf-style luggage stowage compartments common to older style aircraft.

Abstract: Particular embodiments comprise a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to it through the opened side doorway without removing the original door. Once the fixed position or articulated strut is bolted to the AMP, a one piece or segmented two piece pressurized door plug indented along its lower periphery to accommodate the protruding form factor of the fixed position or articulated strut is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft.

Abstract: Overhead stowage compartments are provided for an aircraft. The stowage compartments feature an opening device that can be displaced or rolled up. This may make it possible to prevent lights or air outlets from being covered by pivoting a door upward, as well as to preserve the headroom during the opening process and to prevent collisions between the doors. The architecture of the aircraft may be optimized in this fashion.

Abstract: A method and apparatus comprising a monolithic composite structure, a first edge of the monolithic composite structure, and a second edge of the monolithic composite structure. The first edge of the monolithic composite structure has a first shape configured to be connected to a structure in a vehicle. The second edge of the monolithic composite structure has a second shape configured to be connected to a body of the vehicle.

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

Abstract: In specific embodiments, a vehicle propellable through fluids comprises a main work section and a plurality of propulsion units. The main work section includes a payload support hub, a payload support structure rotatable in 360° about the payload support hub in at least one axis, and a core including at least one microprocessor, the core at least partially nested within the payload support hub. The at least one microprocessor is adapted to substantially maintain an orientation of the payload support structure relative to a horizon line as the vehicle is propelled. One or more payloads are mountable on the rotatable payload support structure.