Abstract: Methods for fabricating semiconductor structures and contacts to semiconductor structures are provided. A method comprises providing a substrate and forming a gate stack on the substrate. The gate stack is formed having a first axis. An impurity doped region is formed within the substrate adjacent to the gate stack and a dielectric layer is deposited overlying the impurity doped region. A via is etched through the dielectric layer to the impurity doped region. The via has a major axis and a minor axis that is perpendicular to and shorter than the major axis. The via is etched such that the major axis is disposed at an angle greater than zero and no greater than 90 degrees from the first axis. A conductive contact is formed within the via.

Abstract: A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

Abstract: A rack for securing containers includes a plurality of bays into which one or more containers are received. The rack includes an upper section and a lower section defining a bay therebetween. The bay has a concave support surface for supporting an object. A plurality of columns connect the upper section to the lower section. The upper section and the lower section each include a plurality of complementary interlocking members aligned with the plurality of columns, such that the interlocking members on the upper section would interlock with the interlocking members on the lower section of a similar rack stacked thereon. Each bay may include a resilient member, such as an expandable clamp or a resilient bumper.

Abstract: A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

Abstract: A method for manufacturing a semiconductor component using a sacrificial masking structure. A semiconductor device is formed from a semiconductor substrate and a layer of dielectric material is formed over the semiconductor substrate and the semiconductor device. The layer of dielectric material may be formed directly on the semiconductor substrate or spaced apart from the semiconductor substrate by an interlayer. Posts or protrusions having sidewalls are formed from the layer of dielectric material. An electrically insulating material that is preferably different from the layer of dielectric material is formed adjacent the sidewalls of the posts. The electrically insulating material is planarized and the posts are removed to form openings that may expose a portion of the semiconductor device or a portion of the interlayer material. An electrically conductive material is formed in the openings.

Abstract: Methods and structures are provided for a dual-bit EEPROM semiconductor device. The dual-bit memory device comprises a semiconductor substrate, a tunnel oxide disposed on the semiconductor substrate and first and second spaced apart floating gates that are disposed on the tunnel oxide. An interlayer dielectric layer contacts the tunnel oxide layer at a position between the first and second spaced apart floating gates and electrically isolates the first and second spaced apart floating gates. A control gate contacts the interlayer dielectric layer between the first and second spaced apart floating gates.

Abstract: A method and system of controlling a process from run-to-run for semiconductor manufacturing. The method of control utilizes a process model to establish a relationship between process control input data and process control output data. The method of control involves minimizing the difference between target process control output data and process control output data predicted by applying the process model to the new process control input data.

Abstract: A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

Abstract: A golf club apparatus includes a head member which includes a ball striking portion and a shaft connection portion which is attached to the ball striking portion. The shaft connection portion includes head-mounted connector portion. A club shaft includes a shaft-mounted connector portion for connection to the head-mounted connector portion. A force-sensing-to-illumination-producing system is supported by the club shaft. The force-sensing-to-illumination-producing system senses a ball-striking force on the ball striking portion and provides an illumination signal on the club shaft which is representative of the ball striking force on the ball striking portion. A plurality of interchangeable head members, having different weights, can be selectively connected to the club shaft.

Abstract: A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

Abstract: A control strategy for a gas turbine engine which exchanges future lifetime of the engine for present thrust. Gas turbine engines, such as those used in aircraft, sometimes incur damage, as when they ingest birds, or are struck with ballistic objects fired by an enemy. The invention detects the damage, and invokes a control strategy wherein the engine is operated in a more harsh manner, thereby sacrificing a significant part of the remaining lifetime of the engine, in order to obtain thrust currently.

Abstract: A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

Abstract: A method and apparatus for detecting an impending failure of a process sensor is provided. The method includes determining a sensor output noise component, and comparing the output noise component to a historical sensor output noise signature based on at least one of the range of span of the sensor and the process operating conditions. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor wherein the processor is programmed to execute a software product code segment that includes a comparator, a data historian, an isolator module, and a limit module. The computing device is configured to detect impending failure of a sensor using an output signal noise component of the sensor and wherein the sensor senses a parameter of a process associated with the computing device.

Abstract: A control strategy for a gas turbine engine which exchanges future lifetime of the engine for present thrust. Gas turbine engines, such as those used in aircraft, sometimes incur damage, as when they ingest birds, or are struck with ballistic objects fired by an enemy. The invention detects the damage, and invokes a control strategy wherein the engine is operated in a more harsh manner, thereby sacrificing a significant part of the remaining lifetime of the engine, in order to obtain thrust currently.

Abstract: A control strategy for a gas turbine engine which exchanges future lifetime of the engine for present thrust. Gas turbine engines, such as those used in aircraft, sometimes incur damage, as when they ingest birds, or are struck with ballistic objects fired by an enemy. The invention detects the damage, and invokes a control strategy wherein the engine is operated in a more harsh manner, thereby sacrificing a significant part of the remaining lifetime of the engine, in order to obtain thrust currently.

Abstract: A sensor in an engineering system can be tested to detect, isolate and accommodate faults. Initially, a modeled sensor value of each actual sensor value is generated as a function of a plurality of other sensors. An absolute value of a difference between the actual sensor value and the modeled sensor value is then computed and compared to a predetermined threshold. A sensor fault is detected if the difference is greater than the predetermined threshold. Once a sensor fault is detected, it is isolated using hypothesis testing and maximum wins strategies. After the fault is isolated, the fault is accommodated by substituting the modeled sensor value for the actual sensor value.

Abstract: A method is provided for determining an etch endpoint. The method includes collecting intensity data representative of optical emission spectral wavelengths during a plasma etch process. The method further includes analyzing at least a portion of the collected intensity data into at most first and second Principal Components with respective Loadings and corresponding Scores. The method also includes determining the etch endpoint using the respective Loadings and corresponding Scores of the second Principal Component as an indicator for the etch endpoint using real-time Principal Components Analysis applied to optical emission spectral data from a previous portion of the plasma etch process.

Abstract: A control strategy for a gas turbine engine which exchanges future lifetime of the engine for present thrust. Gas turbine engines, such as those used in aircraft, sometimes incur damage, as when they ingest birds, or are struck with ballistic objects fired by an enemy. The invention detects the damage, and invokes a control strategy wherein the engine is operated in a more harsh manner, thereby sacrificing a significant part of the remaining lifetime of the engine, in order to obtain thrust currently.

Abstract: A control system trims a gas turbine engine in real-time to provide a desired amount of thrust. The control system includes a controller coupled to the engine for receiving inputs from the engine regarding a status of the engine. The controller includes a processor and a non-volatile memory coupled to the processor. The processor is programmed to execute control logic. An engine power schedule representing values for a controlled variable is stored in the memory.

Abstract: A method is provided for determining an etch endpoint. The method includes collecting intensity data representative of optical emission spectral wavelengths during a plasma etch process. The method further includes analyzing at least a portion of the collected intensity data into at most first and second Principal Components with respective Loadings and corresponding Scores. The method also includes determining the etch endpoint using the respective Loadings and corresponding Scores of the second Principal Component as an indicator for the etch endpoint using Principal Components Analysis applied to archived optical emission spectral data.