Abstract: An aircraft barrel lay-up assembly is provided comprising a barrel mandrel assembly having a contiguous outer barrel lay-up surface. A minor barrel outer surface element is movable between a minor barrel engaged position and a minor barrel disengaged position and forms a minority portion of the contiguous outer barrel lay-up surface when in the engaged position. A major barrel outer surface element is movable between a major barrel engaged position and a major barrel disengaged position. The major barrel outer surface has a first major barrel surface end and a second major barrel surface end moving together to reduce an effective major barrel outer surface circumference when in the major barrel disengaged position. A composite ply assembly is formed around the barrel mandrel circumference and cured while coincident to form a composite barrel element.

Abstract: A reclosable bag having a top flap with holes configured to allow a stack of such bags to be mounted on a wicket or a pair of dispensing posts, and having a slider-actuated zipper (e.g., a string zipper) installed in a mouth at the top of the bag. The wicket flap is suspended between two zones of attachment generally located at opposite ends of the mouth of the bag. In one embodiment, the flap is attached to the slider end stops stomped in opposing ends of the zipper.

Abstract: A process for producing a carbonyl compound involves allowing water to undergo phase transition to a supercritical or subcritical state in the presence of an alcohol compound so as to produce/generate water-derived hydrogen and at the same time convert the alcohol compound into a corresponding carbonyl compound. Specifically, the process is carried out by introducing the alcohol in a reaction tube along with water and heating and/or pressurizing the mixture of the alcohol and the water to bring the water into a subcritical or supercritical state. In this manner, water-derived hydrogen is produced and the alcohol is converted to a corresponding carbonyl compound. The process is preferably carried out in an oxygen-free environment.

Abstract: A tamper-evident reclosable bag having a pull tab feature that facilitates opening of a header by a consumer. The pull tab feature is provided by an offset between the top and bottom webs (or front and rear walls) of the package. One web has a cutout while the other web has a portion that overlaps the cutout. The offset provides a simple means for the consumer to grasp only one of the webs of the package and then pull the webs apart or peel the offset web away from the cutout web. The peeled-away layer can be provided with a line of weakened tear resistance, allowing a section of the header to, at the same time, be torn off the package. After the tamper-evident seal provided by the header is broken, the consumer can open the zipper, gaining access to the contents of the package.

Abstract: An apparatus for the application of aerospace composite laminates 10 is provided, including a non-contaminating outer layer 24 and an insulated base 12. The present invention further includes a constant temperature heating element 22 positioned between the non-contaminating outer layer 24 and the insulated base 12. A battery pack 32 is positioned within the insulated base 12 to power the constant temperature heating element 22. The present invention can further include an ergonomic element 34 mounted to the insulated base 12 to facilitate handling of the apparatus 10 for the application of aerospace composite laminates.

Abstract: A micro-gyroscope (10) having closed loop output operation by a control voltage (Vty), that is demodulated by a drive axis (x-axis) signal Vthx of the sense electrodes (S1, S2), providing Coriolis torque rebalance to prevent displacement of the micro-gyroscope (10) on the output axis (y-axis) Vthy˜0. Closed loop drive axis torque, Vtx maintains a constant drive axis amplitude signal, Vthx. The present invention provides independent alignment and tuning of the micro-gyroscope by using separate electrodes and electrostatic bias voltages to adjust alignment and tuning. A quadrature amplitude signal, or cross-axis transfer function peak amplitude is used to detect misalignment that is corrected to zero by an electrostatic bias voltage adjustment. The cross-axis transfer function is either Vthy/Vty or Vtnx/Vtx.

Abstract: One advantageous embodiment of the present invention is an integrated transport system (14) for moving an object (20) in an aircraft (10) between a main cabin (16) and an overhead cabin (18) via a shaft (24) in connection therebetween. This integrated transport system (14) includes a single-unit gantry-lift device (42) with an object carrier (32) for receiving the object (20). This object carrier (32) has one or more restraint members (34, 38) for securing the object (20) in the object carrier (32) and preventing the object (20) from inadvertently tipping or falling out of the object carrier (32). In this embodiment, the single-unit gantry-lift device (42) further includes a lift device (46) for moving the object carrier (32) generally along a longitudinal axis (22) of the shaft (24) and a gantry device (44) for moving the object carrier (32) generally along a first axis (26) of the overhead cabin (18) and/or a second axis (28), which is disposed generally perpendicular to the first axis (26).

Abstract: An automatic level control circuit exhibits a closed loop response that does not change as a function input power operating point. This allows the designer to set the closed loop response and have that response held fixed with respect to input power operating point. The loop response depends solely on the loop error and the loop gain. The loop error is scaled with the iterative loop stress signal.

Abstract: An anti-personnel airborne radar application for ultra slow target tracking is provided. The anti-personnel airborne radar application includes a rotorcraft and a signal processing system. The signal processing system includes a radar antenna supported by said rotorcraft, a plurality of phase centers, a conditioning circuit for each phase center, an adaptive signal processor, and an ultra slow target indicator. Each phase center is for receiving reflected radar signals received by the radar antenna. The adaptive signal processor processes the received condition signal from each of the phase centers, allowing the ultra slow target indicator to render tracking reports. A method of detecting human motion over a ground swath is also provided.

Abstract: An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation module (46) is in fluid communication with the heat exchanger (56) and separates inerting gas from the pressurized air. A controller (40) controls flow of the inerting gas from the air separation module (46) to the fuel tanks (16).

Abstract: A semiconductor device having at least one layer of a group III–V semiconductor material epitaxially deposited on a group III–V nucleation layer adjacent to a germanium substrate. By introducing electrical contacts on one or more layers of the semiconductor device, various optoelectronic and microelectronic circuits may be formed on the semiconductor device having similar quality to conventional group III–V substrates at a substantial cost savings. Alternatively, an active germanium device layer having electrical contacts may be introduced to a portion of the germanium substrate to form an optoelectronic integrated circuit or a dual optoelectronic and microelectronic device on a germanium substrate depending on whether the electrical contacts are coupled with electrical contacts on the germanium substrate and epitaxial layers, thereby increase the functionality of the semiconductor devices.

Abstract: Methods and apparatus for controlling the registration of one elongated continuous structure (e.g., plastic zipper) with attachments or formed features (e.g., sliders or pre-seals) as it is fed to a sealing station, where it is joined to another elongated continuous structure (e.g., packaging film) with formed features (e.g., thermoformed pockets). The latter elongated continuous structure will be intermittently advanced through the machine, pulling the former elongated continuous structure joined thereto forward. Registration is accomplished by tacking the respective elongated continuous structures together while the respective features on the elongated continuous structures are in proper registration. After tacking, the respective portions of the elongated continuous structures immediately downstream of the tack zone are advanced to the sealing station in proper registration.

Abstract: A system and a method for noninvasive ECG detection and diagnosis. The system comprises a multiplicity of electrodes applied to a patient, a data acquisition system for acquiring high-resolution ECG data from the patient; and a processor programmed to process the acquired data in accordance with two or more different ECG analysis algorithms, and then derive a prediction score for a particular clinical end point as a function of the respective results of those ECG analysis algorithms.

Abstract: A method of manufacture comprising the steps of extruding a zipper part comprising a plastic closure member that has an interlockable profile and that has a side opposite to the profile; and joining a piece of plastic material to the side of the closure member. The piece is disposed entirely within an elevational range bounded by top and bottom edges of the closure member and is designed to function as a slider end stop. The end stop piece can be joined to the side of the plastic closure member by any one of the following techniques; heating the plastic to a softening temperature and pressing the piece against the softened portion; gluing the piece to the side of the closure member; fastening the piece to the closure member; or injection molding the piece onto the side of the closure member.

Abstract: A power control system (12) for a satellite (10 includes a high power amplifier circuit (28) that receives a saturated power output adjustment signal. The amplifier circuit (28) includes a programmable circuit (70). An electronic power conditioner (56) is coupled to the programmable circuit (70) and is configured to reset an operating set-point of said high power amplifier circuit (28) in response to the saturated power output adjustment signal. A high power amplifier (46) has a variable output power range and amplifies a received signal in response to change in the operating set-point. A channel amplifier (44) is coupled to the programmable circuit (70) and is configured to gain offset the received signal in response to change in the operating set-point.

Abstract: A power control system for a satellite receiving radio-frequency signals includes a digital processor and a traveling wave tube amplifier system and corresponding traveling wave tube. An anode voltage of the traveling wave tube amplifier system is used to modulate or saturate the current of the electron beam of the traveling wave tube so that the output power of the traveling wave tube amplifier system, from the saturated electron beam, is proportional to a waveform envelope of the radio-frequency signals. The digital processor controls anode and RF input signal amplitudes to the traveling wave tube and predicts necessary corrections.

Abstract: An interior cabin configuration determination system (10) includes multiple objects (16), including two or more monuments or passenger service units, that are within an interior cabin (13). The objects (16) include card readers (12). Object controllers (18) are coupled to the card readers (12) and determine the position of the objects (18) in response to the position information on the cards (12). A remotely located controller (20) determines the configuration of the objects (18) in response to the position information.

Abstract: A system (18) includes: a) A vehicle (12) includes an attitude or angular velocity control system (38), a plurality of star trackers or star sensors (22) each having a field of view (28); b) a memory (30) having a star catalog (32), an allocated area for a star pair catalog (58) and a reference table (56) stored therein; and c) a processor (24) coupled to the attitude or angular velocity control system (38), the star trackers or star sensors (22), and the memory (30). The processor (24) populates the star pair catalog (58), using the method described herein. The processor (24) then periodically determines the vehicle inertial attitude or angular velocity or sensor alignment, based, in part, on the star pair catalog (58) and reference table (56). The novel ability of the software to autonomously populate the star pair catalog (58) allows users to avoid uploading a large amount of data, and the problems associated with such an upload.