Abstract: Systems are provided for generating, modifying and using SBOMs for facilitating risk assessment and threat mitigation for corresponding programs, and particularly for large programming builds. The creation and modification of the SBOMs includes processes for omitting declarations referenced in chunk SBOMs of program chunks incorporated into a final programming build associated with a build SBOM, but which are not actually utilized by the final programming build, as well as processes for adding new declarations for code segments that are not declared in the related chunk SBOMs, even though the code segments are utilized by the final programming build. Systems are also configured to use SBOMs in combination with configuration restriction records to assess and resolve threat events in a manner that can prevent unnecessary remedial actions for threat events that appear to be relevant to one or more files or dependencies incorporated into a program.

Abstract: Systems are provided for generating, modifying and using SBOMs for facilitating risk assessment and threat mitigation for corresponding programs, and particularly for large programming builds. The creation and modification of the SBOMs includes processes for omitting declarations referenced in chunk SBOMs of program chunks incorporated into a final programming build associated with a build SBOM, but which are not actually utilized by the final programming build, as well as processes for adding new declarations for code segments that are not declared in the related chunk SBOMs, even though the code segments are utilized by the final programming build. Systems are also configured to use SBOMs in combination with configuration restriction records to assess and resolve threat events in a manner that can prevent unnecessary remedial actions for threat events that appear to be relevant to one or more files or dependencies incorporated into a program.

Abstract: Systems are provided for generating, modifying and using SBOMs for facilitating risk assessment and threat mitigation for corresponding programs, and particularly for large programming builds. The creation and modification of the SBOMs includes processes for omitting declarations referenced in chunk SBOMs of program chunks incorporated into a final programming build associated with a build SBOM, but which are not actually utilized by the final programming build, as well as processes for adding new declarations for code segments that are not declared in the related chunk SBOMs, even though the code segments are utilized by the final programming build. Systems are also configured to use SBOMs in combination with configuration restriction records to assess and resolve threat events in a manner that can prevent unnecessary remedial actions for threat events that appear to be relevant to one or more files or dependencies incorporated into a program.

Abstract: Methods and systems for direct lithographic pattern definition based upon electron beam induced alteration of the surface chemistry of a substrate are described. The methods involve an initial chemical treatment for global definition of a specified surface chemistry (SC). Electron beam induced surface reactions between a gaseous precursor and the surface are then used to locally alter the SC. High resolution patterning of stable, specified surface chemistries upon a substrate can thus be achieved. The defined patterns can then be utilized for selective material deposition via methods which exploit the specificity of certain SC combinations or by differences in surface energy. It is possible to perform all steps in-situ without breaking vacuum.

Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Abstract: A fluid transport coupling subcomponent can include a body having a first axial end with a first axial face, a second axial end, and a hollow conduit extending between the first and second axial ends, a tongue extending longitudinally from the first axial face; and a groove recessed into the first axial face. The tongue can extend a distance, DT1, from the first axial face and the groove can extend a distance, DG1, into the body from the planar face, where DG1 and DT1 can be different.

Abstract: Methods and systems for direct lithographic pattern definition based upon electron beam induced alteration of the surface chemistry of a substrate are described. The methods involve an initial chemical treatment for global definition of a specified surface chemistry (SC). Electron beam induced surface reactions between a gaseous precursor and the surface are then used to locally alter the SC. High resolution patterning of stable, specified surface chemistries upon a substrate can thus be achieved. The defined patterns can then be utilized for selective material deposition via methods which exploit the specificity of certain SC combinations or by differences in surface energy. It is possible to perform all steps in-situ without breaking vacuum.

Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Abstract: Methods and systems for direct lithographic pattern definition based upon electron beam induced alteration of the surface chemistry of a substrate are described. The methods involve an initial chemical treatment for global definition of a specified surface chemistry (SC). Electron beam induced surface reactions between a gaseous precursor and the surface are then used to locally alter the SC. High resolution patterning of stable, specified surface chemistries upon a substrate can thus be achieved. The defined patterns can then be utilized for selective material deposition via methods which exploit the specificity of certain SC combinations or by differences in surface energy. It is possible to perform all steps in-situ without breaking vacuum.

Abstract: A fluid transport coupling subcomponent can include a body having a first axial end with a first axial face, a second axial end, and a hollow conduit extending between the first and second axial ends, a tongue extending longitudinally from the first axial face; and a groove recessed into the first axial face. The tongue can extend a distance, DT1, from the first axial face and the groove can extend a distance, DG1, into the body from the planar face, where DG1 and DT1 can be different.

Abstract: Methods and systems for direct lithographic pattern definition based upon electron beam induced alteration of the surface chemistry of a substrate are described. The methods involve an initial chemical treatment for global definition of a specified surface chemistry (SC). Electron beam induced surface reactions between a gaseous precursor and the surface are then used to locally alter the SC. High resolution patterning of stable, specified surface chemistries upon a substrate can thus be achieved. The defined patterns can then be utilized for selective material deposition via methods which exploit the specificity of certain SC combinations or by differences in surface energy. It is possible to perform all steps in-situ without breaking vacuum.

Abstract: A lighting apparatus for an AC voltage supply is provided. A rectifier module of the apparatus converts an AC voltage from the AC voltage supply into a rectified supply voltage. A diode cascade of the apparatus has multiple diode cascade sections connected in series and each having an LED. Each diode cascade section has a connectable bypass device for bypassing the diode cascade section. The diode cascade section is in an illuminated state when the bypass device is deactivated and a dark state when the bypass device is activated. A current source module is provided for stabilizing the cascade current through the diode cascade to a setpoint value. At least one diode cascade section has a control device, which has a switching device for converting the detected illuminated state into a switching signal for reducing the setpoint value.

Abstract: The object of the present invention consists in proposing a lighting apparatus for an AC voltage supply which is characterized by a homogeneous light emission.

Abstract: A lighting device for an AC power supply comprising at least two lighting groups, wherein each lighting group has a group input and a group output and at least one LED, wherein the at least one LED is arranged between the group input and the group output, wherein the lighting groups are connected to one another in series.

Abstract: The invention relates to an arrangement for heating a portion of the cabin floor in an aircraft cabin, wherein the cabin floor has an upper side which can be walked on and a lower side opposite the upper side, comprising a fuel cell and, connected or connectable thereto, a removal device with which a fluid heated by waste heat of the fuel cell is removed from the fuel cell and supplied to a cavity which is adjacent to the lower side of the cabin floor or is located in the cabin floor, and therefore the portion of the cabin floor is heated.

Abstract: An on-board supply system (10) for use in an aircraft comprises a fuel cell unit (20) for generating electrical energy and heat energy, and at least one consumer system (100). The fuel cell unit (20) is designed to release heat energy in the form of hot air, and the consumer system (100) is designed to absorb the electrical energy and the heat energy in the form of hot air. The fuel cell unit (20) can comprise at least one low-temperature (LT) fuel cell (30) and at least one high-temperature (HT) fuel cell (40), which can both (30, 40) be designed to be regulated to their respective operating temperature in operation by means of air cooling, and an air cooling inlet (44) of the HT fuel cell (40) can be connected in fluid communication with an air cooling outlet (36) of the LT fuel cell (30).

Abstract: The present invention is directed to an electrical supply apparatus having an input for connecting the electrical supply apparatus to a mains supply which provides an alternating voltage as input voltage, having an output for connecting the electrical supply apparatus to a load, wherein the output provides a DC voltage as output voltage, having a rectifier which rectifies the input voltage to form a rectified input voltage, having a PFC module which comprises a smoothing device for smoothing the rectified input voltage and an active power factor correction device, wherein the power factor correction device is designed to form a time-dependent supply current for the smoothing device depending on a time-dependent current form signal in such a way that a time-dependent input current in the PFC module is matched to the current form signal, wherein the current form signal is produced by an analogue circuit.

Abstract: A spa system comprises an electrically powered heater. The electrically powered heater comprises a heating element capable of drawing a rated current when switched on to an AC line voltage. An electronic control system is programmed to control the heating element to draw less than the rated current.

Abstract: An on-board supply system (10) for use in an aircraft comprises a fuel cell unit (20) for generating electrical energy and heat energy, and at least one consumer system (100). The fuel cell unit (20) is designed to release heat energy in the form of hot air, and the consumer system (100) is designed to absorb the electrical energy and the heat energy in the form of hot air. The fuel cell unit (20) can comprise at least one low-temperature (LT) fuel cell (30) and at least one high-temperature (HT) fuel cell (40), which can both (30, 40) be designed to be regulated to their respective operating temperature in operation by means of air cooling, and an air cooling inlet (44) of the HT fuel cell (40) can be connected in fluid communication with an air cooling outlet (36) of the LT fuel cell (30).

Abstract: A fuel cell is provided, with an anode device having a fuel inlet, a cathode device having an oxidizing agent inlet, and a membrane arranged between the anode device and the cathode device. The fuel cell has means for self-regulating the output power of the fuel cell, which counteract a reduction in output power or regulate output power substantially independently of the fuel cell service life and operating temperature. The means can have at least one bypass diode connected electrically to the anode device and the cathode device and/or at least one fuel feed device with a self-regulating fuel feed, which has a first thermally expansible element, and/or at least one oxidizing agent feed device with a self-regulating oxidizing agent feed, which has a second thermally expansible element.