Abstract: A method for the direct manufacture of aerospace duct elements is provided comprising executing a single build run on a build chamber using direct fabrication technology to generate at least one duct section. The at least one duct section is generated by forming a plurality of partial cylinder duct segments orientated within the build chamber in a nested arrangement during the single build run, and assembling at least two of the partial cylinder duct segments to form the duct section. During the single build run a plurality of stiffening protrusions are formed on each of the partial cylinder duct segments to improve duct rigidity and to modify flow through the duct section.

Abstract: A method of WWW page retrieval from a web site, comprising entering information associated with the site; and directly displaying said page, using a browser, without any additional user intervention. Preferably, the information is in a non-Latin language. Alternatively or additionally, the information does not meet domain name specifications, for example, being in a free-form format.

Abstract: An aircraft stringer lay-up assembly is provided comprising a first mandrel element having a first mandrel material with a first mandrel coefficient of thermal expansion. A composite ply assembly is laid up onto the first mandrel element to generate a primary lay-up surface. The composite ply assembly comprises a first primary fold-over portion folded onto to the first mandrel right end surface. A second primary fold over portion folds over to the first mandrel left end surface. The first mandrel coefficient of thermal expansion is adapted such that the first mandrel is movable between a first mandrel normal condition and a first mandrel heated condition where the first mandrel right end surface and the first mandrel left end surface move away from each other. The first primary fold-over portion and the secondary primary fold over portion are thereby moved such that wrinkles are pulled out of said primary lay-up surface.

Abstract: A method of winding a length of plastic ribbon (such as a zipper of the type used in reclosable packaging) around a cylinder of a spool having a first flange at one end and a second flange at the other end, comprising the following steps: (a) winding the ribbon with a winding tension in a first range when the portion of the ribbon being wound is within a first volume surrounding a central region of the cylinder; and (b) winding the ribbon with a winding tension in a second range when the portion of the ribbon being wound is within second and third volumes surrounding respective portions of the cylinder disposed between the central region and the first and second flanges respectively. To reduce camber in the portions of the wound ribbon disposed in the second and third volumes, i.e., near the respective spool flanges, the upper limit of the second range of winding tension is less than the lower limit of the first range of winding tension, i.e.

Abstract: A method of transporting and stowing an object within an aircraft comprises inserting the object into a transport unit; activating a first transfer drive system attached to said transport unit; drawing the object into said transport unit via a first motor and a first wheel of said first transfer drive system; conveying said transport unit to a stowage unit; releasing the object from the transport unit; and inserting the object into said stowage unit.

Abstract: A spacecraft emulation system for emulating the operation of a spacecraft and the operation of a plurality of ground stations is coupled to spacecraft status and control clients that request connections to one of the plurality of simulated ground station ranging and tracking servers. The connection requests are made to a common address with a port address that is unique to a specific ground station. Separate range servers and tracking servers are instantiated for each ground station and return data specific to the ground station. The spacecraft emulation system determines ranging and tracking data for the plurality of simulated ground stations but supplies the data on a ground station by ground station basis. The status and control system transparently determines which ground station is simulated.

Abstract: A terminal (14) for an airport (13) includes multiple servicing levels (82, 102). A ground support service sub-system is coupled to the servicing levels (82, 102) and is configured to mate with a service opening (26) of the aircraft (12). The ground support service sub-system provides services to the aircraft (12) through the service opening (26) and on the servicing levels (82, 102).

Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

Abstract: A flaw and foreign object debris (FOD) detection system (11) for use during fabrication of a structure (12) includes an illumination device (13). The illumination device (13) is configured to be in proximity with a fabrication system (10) and illuminates a portion (18) of the structure (12). The illumination device (13) directs light rays (16) at acute angles relative to the portion (18). A detector (14) monitors the portion (18) and detects FOD in the portion (18) during fabrication of the structure (12) in response to the reflection of the light rays (16) off of the portion (18).

Abstract: A mobile ground servicing unit (470) includes a stand-alone support structure (471). Wheels (473) are coupled to the support structure (471). The support structure (471) has one or more servicing levels (472, 474) that are associated with services. A ground support service sub-system is coupled to the servicing levels and is configured to mate with a service opening (26?) of an aircraft (12??). The ground support service sub-system provides the services to the aircraft (12??) through the service opening (26?) and on the servicing levels (472, 474).

Abstract: A portable multi-axis load confirmation tool having a rotating ball on the end thereof follows a three-dimensional weld program path therewith. The ball reacts to an internal load cell for verifying weld program path dynamics before an actual program is run with friction stir welding tools. The load cell is connected to instrumentation electronics converting a load cell signal to a digital readout and comparing the load cell signal to weld program load requirements. The tool integrates into a tool holder loaded on a friction stir welding spindle for simulating an actual friction stir welding tool.

Abstract: A mandrel is disclosed for fabricating a monolithic composite nacelle panel for use on an airplane. Also disclosed is the method of constructing the mandrel, the method of assembling the mandrel, and the method of disassembling the mandrel.

Abstract: A self-locating feature for a pi-joint assembly is provided. The pi-joint assembly includes a substructure, a member coupled to the substructure. The substructure includes one or more land extending above one of a front side and a back side of the substructure. The land includes an outer surface, a depth location control surface and an edge location control surface. The member includes a base, a pair of axially elongated leg extending from the base to define a channel therebetween, and one or more notch located in one of the pair of axially elongated leg.

Abstract: A storage bag comprises: first and second panels joined or connected on three sides and having a mouth on a fourth side; a pair of zipper strips respectively joined to the first and second panels in the region of the mouth, each zipper strip comprising respective upper and lower zipper profiles; resealable means joined to at least one of the zipper strips in a region between the upper and lower zipper profiles; and a slider that pushes the respective pairs of zipper profiles together and reseals the resealable means as the slider travels along the mouth of the bag. In one embodiment, the resealable means comprise a layer of adhesive material that adheres to the base web of the opposing zipper strip as the moving slider presses the adhesive material and base web together. In another embodiment, the resealable means comprise first and second layers of cohesive material that cohere to each other as the moving slider presses the layers of cohesive material together.

Abstract: The “discrete frequency stir” (DFS) method provides improved mode stir testing of electromagnetic characteristics of an enclosure/cavity. Adequate sampling of the electric field inside the enclosure/cavity is provided by electronic perturbation or “stirring” of the field with a short duration, continuous wave, radiated source where the wave frequency is stepped in small steps across a frequency range of interest. The frequency steps are selected to be at least slightly larger than the resonant mode bandwidth associated with the given enclosure/cavity in order to provide statistically independent measurements. A stirring bandwidth is selected to encompass a statistically significant number of these measurement samples while maintaining adequate frequency resolution. A statistical evaluation of the measured field is then performed over this stirring bandwidth.

Abstract: A reclosable package comprising front and rear panels extending between top and bottom transverse seals, the front panel having a line or lines of weakened tear resistance for forming an opening, through which a zipper can be accessed. The zipper is suspended from the top transverse seal and attached to the front panel at a lower elevation. At least a major portion of the base strip of a forward zipper part is disposed between the front panel and the base strip of a rearward zipper part. Respective upper portions of the zipper base strips are joined to each other in the top transverse seal. A lower portion of the base strip of the forward zipper part is joined to the front panel in a transverse band-shaped zone of joinder. No portion of the base strip of the rearward zipper part is joined to the rear panel outside of the top transverse seal.

Abstract: A latch handle assembly includes a bezel disposed within a panel and a handle having a center portion, a first grip portion, and a second grip portion. The center portion is disposed between the first grip portion and the second grip portion. The center portion pivotally mounts the handle within the bezel.

Abstract: An aircraft (12) includes a servicing opening (26) and multiple service levels (82, 102). The service levels (82, 102) include a noncargo-based service level (82). The service levels (82, 102) are accessible through the service opening (26). An aircraft onboard primary servicing system (66) includes a primary service sub-system (151). An aircraft primary service coupler (154) is configured to attach to a corresponding terminal primary service coupler (152). The aircraft primary service coupler (154) and the terminal primary service coupler (152) providing at least one primary service therethrough.