Abstract: A method of making a tailored blank comprising the following steps: (a) friction welding first and second structural members together at a substantially right angle with respect to each other to form an intersection comprising a first joining surface formed by adjoining bottom faces of the first and second structural members, and a second joining surface formed by an angled face of the first structural member that is disposed at a first oblique angle relative to the bottom face of the first structural member; (b) friction welding the first joining surface of the intersection to a first portion of a surface of a base member; and (c) concurrently linear friction welding first and second joining surfaces of a third structural member to the second joining surface of the intersection and to a second portion of the surface of the base member respectively.

Abstract: A secure network server having an embedded Hyper-Text Transfer Protocol (HTTP) server that is not within its trusted security functionality and that is used to configure the SNS security and networking features.

Abstract: A device for stowing and deploying a handheld device such as a telecommunications handset within an aircraft or other vehicle has a housing, a pivoting cradle attached to the inner surface of the housing, means for limiting the range of permitted pivoting motion of the cradle within the housing, optional biasing means such as a coil spring between the housing and the pivoting cradle, and means for mounting the housing to a secure place in the aircraft. The cradle has an elongate base with a handset receiving section, and a pivoting mount affixed or integrally molded on each side of the housing. The symmetrical pivoting mount may be a series of at least two slots arrayed in a radius from the geometric pivot point, i.e., the axis of rotation of the handset cradle.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: A hub fairing system (12) for a stopped-rotor aircraft (10) having a fuselage (14) including a hub (16). The hub (16) is mechanically coupled to the fuselage (14) and to multiple blades (40) and is rotated by an engine (22). A retractable fairing (60, 64) covers a portion of the hub (16). An actuator (26) is coupled to the fairing (60, 64). A controller (28) is coupled to the actuator (26) and retracts the fairing (60, 64). A method of reducing drag on the aircraft includes transitioning between a rotary-wing mode and a fixed-wing mode. The fairing (60, 64) is deployed over a portion of the hub (16) upon the completion of the transition between flight modes.

Abstract: An apparatus for holding an aerospace structure, having an edge and a surface, includes a base. Coupled to the base is an edge support adapted to releasably engage the edge of the structure. Also coupled to the base is a stanchion. Moveably coupled to the stanchion is a surface support adapted to support the surface of the structure when the edge of the structure is retained by the edge support.

Abstract: A stress concentration reduction system includes a hoop tension finger doubler coupled to a lap splice. The lap slice is formed by an first panel overlapped by a second panel. The hoop tension finger doubler is formed to fit against the panels flushly.

Abstract: The present invention is to provide an optical modulating system for generating a signal of a frequency (f0+2fm) and a signal of a frequency (f0?2fm) and suppressing a signal of a frequency (f0) by a DSB-SC modulator. A fourth harmonic generating system for solving the above problem comprises a first DSB-SC modulator (2) a second DSB-SC modulator (3) and a signal control section (5) for controlling a modulating signal from a signal source (4) for generating modulating signals applied to the first and second DSB-SC modulators (2,3) so that a lower side-band signal (f0) generated by modulating the upper side-band signal of the DSB-SC modulator (2) by the DSB-SC modulator (3) and an upper side-band signal (f0) generated by modulating the lower side-band signal of the DSB-SC modulator (2) by the DSB-SC modulator (3) cancel each other.

Abstract: A metallurgically formed fluid circuit joint includes a hollow fitting (298), a tubular conduit (297), and a metallurgically formed tube/fitting mesh (296). The tube/fitting mesh (296) includes a fitting portion of the hollow fitting (298) and a tube portion of the tubular conduit (297) that is electromagnetically formed with the fitting portion.

Abstract: The invention is a pump cap that is designed to seat on top of a receptacle, which in at least one example is filled with powder or hair fibers. The cap is fitted on top with a deformable dome with an empty chamber of air within it. The cap has an air inlet with a check valve that then opens into a wide flared opening into the dome's empty chamber. The air in the dome is pushed past a check valve and down a long passageway into the receptacle to aggressively disturb the powder or hair fibers within the receptacle. The disturbed hair fibers or powder then exits the cap through a third passage with a flared opening that is flush with the bottom of the cap that then exits out the side of the cap.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: A food supportive device (20) for use in microwave heating or cooking of food (10) including a plurality of food contact areas (21) elevated from and substantially integral to a foundation (28) that enables the support of food directly placed on the contact areas, wherein spaces are formed between the elevated food contact areas (21) and the foundation (28) enable the venting or escape of moisture from the food to prevent the food from going soggy.

Abstract: A method of manufacturing a protective cover (24) for a component of a vehicle includes assembling multiple layers to form a charge (22). The charge (22) is formed within a mold (50) of the component to form a multi-contoured laminate (58). The protective cover (24) is separated from the multi-contoured laminate (58). A method of forming a down stream part structure or mold (167) for a component includes assembling multiple layers to form a charge (78). The charge (78) is formed within an original mold of the component to form a multi-contoured laminate (76). A splash is separated from the multi-contoured laminate (76). A protective cover, such as the cover (24), is for a vehicle component and includes a contour holding layer (36) and a protective laminate layer (34). The contour holding layer (36) and the protective laminate layer (34) are formed within a mold of the vehicle component to form the protective cover.

Abstract: An aluminum tubular unit for long-term, leak-free storage of fluids is formed in which an aluminum cap is ultrasonically welded to an end of the aluminum tube. The ultrasonic weld is formed from a device capable of producing a torsional vibration pattern. The ultrasonic welding of the cap to the tube eliminates the use of seals and pins to seal the cap to the tube and further eliminates the need for having a hole in the cap to mechanically couple the respective end cap to the cylindrical tube. Furthermore, since ultrasonic welding does not generate significant heat, highly volatile and flammable fluids can be present within the tube when the caps are ultrasonically welded to the cylindrical body. In addition, one or more fins used may also be welded to the outside diameter of the cylindrical body using a related ultrasonic welding process.

Abstract: One advantageous embodiment of the present invention is a reaction-injection-molded galley cart (10) for an aircraft. This cart (10) includes a body, which is configured to move along a passenger aisle of the aircraft. The body is comprised of a one-piece plastic shell (12) having a first side portion (28), a second side portion (30) spaced apart from the first side portion (28), a top side portion (24) extending between the first side portion (28) and the second side portion (30), and a bottom side portion (32) extending between the first side portion (28) and the second side portion (30). This one-piece plastic shell (12) includes at least one layer (36) of a reaction-injection-molded material.

Abstract: The invention relates to a device for positioning a guiding tube (1) for a nephroscope, said tube consisting of a long aspiration needle (2) which is provided with a closing mandrin (3) and on which an inflatable enlargement device (4) slides, said device especially comprising a cuff (25) which is positioned by sliding along the aspiration needle (2) that is previously inserted into the kidney of the patient. The operation is facilitated by a trocar consisting of cutting blades (19) which enlarge the opening without tearing any flesh. The cuff is then inflated so that the inflatable enlargement device (4) can be used as a guiding means for a guiding tube for a nephroscope during the positioning thereof in the kidney of the patient.

Abstract: A fabrication method of forming a thermoplastic composite laminate material with tailored and varying thickness in a continuous process. This process utilizes automated equipment or hand lay-up to collate parts or components into a multi-layer stack. Each stack contains all plies, including ply build-up areas, tacked in the proper location to maintain orientation and location. The consolidation tooling contains all necessary part features and is coordinated to the customized multiple ply stacks to form a single integrated thermoplastic composite laminate potentially having areas of differing thickness from these multiple ply stacks.

Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

Abstract: An extraction apparatus (40) for the removal of a riveted fastener (12) from a structure (10) includes a shaft (42) and a cutting element (62). The cutting element (62) is mechanically coupled to the shaft (42) and is configured to cut a portion of the riveted fastener (12). The shaft (42) and the cutting element (62) are configured for insertion through an inner channel (24) of the riveted fastener (12). A method of replacing the riveted fastener (12) from the structure (10) includes inserting the extraction apparatus (40) through the inner channel (24). The extraction apparatus (40) is rotated. A portion of the riveted fastener (12) that extends through the structure (10) is removed. A head (20) of the riveted fastener (12) is also removed from the structure (10).