3251results about "Aircraft floors" patented technology

An unmanned aerial vehicle (UAV) for making partial deliveries of cargo provisions includes a UAV having one or more ducted fans and a structural interconnect connecting the one or more fans to a cargo pod. The cargo pod has an outer aerodynamic shell and one or more internal drive systems for modifying a relative position of one or more cargo provisions contained within the cargo pod. Control logic is configured to, after delivery of a partial portion of the cargo provisions contained within the cargo pod, vary a position of at least a portion of the remaining cargo provisions to maintain a substantially same center of gravity of the UAV relative to a center of gravity prior to delivery of the partial portion. Other center of gravity compensation mechanisms may also be controlled by the control logic to aid in maintaining the center of gravity of the UAV.

The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.

A method of manufacturing a monolithic composite wing without using mechanical fasteners is described. The process begins with the formation of a center wing box in combination with a pair of spars, riblets and a pair of skin-molds including the wrapping and binding of the box by means of resin impregnated composite tapes. Next, additional cells are adjoined contiguously on either side of the current framework and an overlap wrapping and bonding process is continued around the current framework. The overlap wrapping and binding procedure provides increased torsion stiffness and reduced structural weight. All cells up to the leading and trailing edges will be included in the assembly process. Conduits to convey fuel, hydraulic fluid and electrical wiring will also be installed in designated cells. Finally, the completed wing will be cured in an autoclave under uniform pressure and temperature.

A chromogenic window panel assembly, and a chromogenic skylight each includes an outer panel and a chromogenic member having an optical property which varies according to an applied signal. A chromogenic light pipe includes a light harvesting member and a chromogenic member having an optical property which varies according to an applied signal. A chromogenic vehicle sunroof, a chromogenic aircraft window assembly, and a chromogenic window assembly each includes a panel having a particular panel contour corresponding to a surface contour and a chromogenic panel having an optical property which varies according to an applied signal. A chromogenic block includes two panels and a chromogenic panel having an optical property which varies according to an applied signal.

Arrangement for producing a three-dimensional product, which arrangement comprises a work table on which said three-dimensional product is to be built up, a powder dispenser which is arranged so as to distribute a thin layer of powder on the work table for forming a powder bed, a radiation gun for delivering energy to the powder, fusing together of the powder then taking place, means for guiding the beam emitted by the radiation gun over said powder bed for forming a cross section of said three-dimensional product by fusing together parts of said powder bed, and a control computer in which information about successive cross sections of the three-dimensional product is stored, which cross sections build up the three-dimensional product, where the control computer is intended to control said means for guiding the radiation gun over the powder bed according to an operating scheme forming a cross section of said three-dimensional body, said three-dimensional product being formed by successive fusing together of successively formed cross sections from by the powder dispenser, and method for producing three-dimensional product using such an arrangement.

A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.

A surveillance window including at least one set of linear polarizer and quarter-waveplate and a reflecting surface. The surveillance window appears dull and opaque to a subject, while allowing a relatively high percentage of light to be transmitted to an observer. Various enhancements including an illuminator and detector, camouflaging, fire resistance, and improvements to the opacity are also described.

A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

A cargo loading logistics system for verifying cargo loaded on an aircraft receives a desired restraint configuration from a database and determines an actual restraint configuration on the aircraft by receiving data from a plurality of machine readable identifiers corresponding to a plurality of install points and data from a plurality of machine readable identifiers corresponding to a plurality of restraints. The cargo loading logistics system then compares the desired restraint configuration with the actual restraint configuration and determines if the aircraft is properly configured to be loaded for an upcoming flight.

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.

A composite material-stiffened panel has a skin obtained by molding a fiber-reinforced resin composite material into a flat skin, stiffeners arranged in rows on one surface of the skin, and a fiber-reinforced resin-composite material stitched on the skin covering the stiffeners. The composite material-stiffened panel can be manufactured as follows: A first fabric material is placed on a tool having a panel-shaped surface. Stiffeners are placed on the first fabric materials. A second fabric material is placed on the stiffeners to cover at least some of the stiffeners. The second fabric materials are reformed to match the shape of the stiffeners. The reformed second fabric material is stitched on the first fabric material along edges of the stiffeners. All the materials are covered with a bagging film for vacuum. Resin is infiltrated into the fabric materials by a RTM or a RFI method. The infiltrated resin is heated to be hardened.

An aircraft is provided comprising a fuselage and a central monitoring system positioned within the fuselage. A plurality of seating elements is also positioned within said fuselage. Each of the plurality of seating elements includes a plurality of seat options integrated into the seating element and an electronics control system integrated into the seating element. The electronics control system includes a seat processor having logic adapted to monitor an operational status of each of the seat options and communicate the operational status to the central monitoring system via wireless communication.

In an anti-hijacking system for autopilot equipped aircraft, a transceiver communicates with at least one remote guidance facility. A panic button is activated by flight crew in case of hijacking. A manager is coupled to the transceiver and the panic button, as well as existing avionics including the aircraft's master computer and autopilot. Optionally, a relay is coupled between the pilot controls and selected aircraft flight systems. The manager recognizes predetermined override inputs, such as activation of the panic button or receipt of override signals from the remote guidance facility. Responsive to the override input, the manager deactivates on-board control of selected aircraft flight systems and the autopilot system, and directs the autopilot to fly the aircraft to a safe landing. Flight routing and landing instructions are obtained from the remote guidance facility, or by self-evaluating nearby airports in view of the aircraft's position and various preestablished criteria.

A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg.

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

The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.

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

Various embodiments of the invention relate generally to systems for providing active vertical control of an airship. More particularly, at least one embodiment of the invention relates to a system for actively controlling the aerostatic lift of an airship by manipulating the ratio of air to lifting gas contained within the airship, and thus the overall mass of the airship. This manipulation is accomplished by actively compressing and / or decompressing the lifting gas or internal air, with the resulting pressure differential borne primarily by the hull and / or an internal pressure tank depending upon the configuration.

A method of forming a structural airframe component for an aircraft and an airframe structural component The method includes placing at least two components (1,2) in abutting relationship with each other and joining them together by friction stir butt welding (3), and the structural airframe component comprises a component manufactured according to the method of the invention.

A method and apparatus for a composite helicopter comprising a rotary wing parent vehicle with various modular cabins detachable therefrom to facilitate various configuration aircraft platforms, dual operation and modular economy.

A passenger cabin of a passenger transport vehicle such as an aircraft includes single passenger seats arranged between an aisle and an outside cabin wall. Each seat is tiltably adjustable between an upright seating configuration and a reclined lying configuration, and is rotatable between a forward-facing orientation facing 0 to 18° relative to the cabin longitudinal axis, and an inwardly-turned orientation facing 50 to 600 relative to the longitudinal axis. The forward-facing orientation is for upright seating during take-off and landing. The inwardly-turned orientation provides additional leg room and sufficient space for the reclined lying configuration. The pitch spacing between seats can be minimized, and total seating capacity is high, while providing substantial space and comfort for each passenger. Screening partitions adjacent to the cabin wall and the aisle provide privacy screening and define a personal space allocated to each seat.

Arrangement for producing a three-dimensional product, which arrangement comprises a work table on which said three-dimensional product is to be built up, a powder dispenser which is arranged so as to distribute a thin layer of powder on the work table for forming a powder bed, a radiation gun for delivering energy to the powder, fusing together of the powder then taking place, means for guiding the beam emitted by the radiation gun over said powder bed for forming a cross section of said three-dimensional product by fusing together parts of said powder bed, and a control computer in which information about successive cross sections of the three-dimensional product is stored, which cross sections build up the three-dimensional product, where the control computer is intended to control said means for guiding the radiation gun over the powder bed according to an operating shceme forming a cross section of said three-dimensional body, said three-dimensional product being formed by successive fusing together of successively formed cross sections from by the powder dispenser, and method for procducing three-dimensional product using such an arrangement.

A passenger seating arrangement includes a first seat unit, facing in a first direction; a first ottoman having a first support surface positioned to receive the feet of a passenger seated in the first seat unit; a second seat unit facing in a second direction generally opposite to the first direction; and a second ottoman disposed laterally adjacent to the first ottoman and having a second support surface positioned to receive the feet of a passenger seated in the second seat unit.

Interior architectural structures and lighting for aircraft, particularly commercial passenger airplanes. Light diffusers and ceiling panels in a “wing-shape” and other secondary panels are utilized to create different interior designs and structures. A permeable secondary panel is utilized in one passenger cabin in order to provide a more private-type space. An enlarged ceiling arch with blended curves forming a “wing-type” configuration provides a more spacious cabin arrangement. Other features include air and light diffusers, passenger service modules, a “shelf”-like configuration and lighting above the airplane entrance / exit door, and bulkheads and monuments positioned at various positions in the cabin.

Integrally stiffened and formed, load carrying structures comprising a plurality of elongated thin-walled tubes placed co-extensively in a complementary side-by-side fashion which together form a hollow structure having a desired external contour. Integral skins forming the external and internal surfaces of the structure cooperatively therewith. The structure can be formed with an underlying internal support member spanning the interior of the load carrying structure, thereby connecting opposite sides of the structure together. Also, each of the tubes are wound with fibers in controlled orientations generally paralleling the direction of the loads applied to the tubes to optimize the strength to weight ratio of the tubes.

A vehicle seating arrangement can comprise a fore-facing lower seating assembly, an aft-facing lower assembly, and an upper seating assembly positioned between the fore-facing and aft-facing lower assemblies. The lower and upper assemblies can be configured to form a 3-seat unit in which a portion of a seat of said fore-facing and aft-facing lower seat assemblies underlaps a portion of an upper seating assembly. At least one of the fore-facing and aft-facing lower assemblies can be angled with respect to the upper seating assembly to shorten the overall linear dimension of the 3-seat unit and provide egress areas for lower passengers to aisle access. A vertical member can be configured to attach to the upper seating assembly and to a ceiling structure to reduce the load on the floor.