Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.

Abstract: A system and method for capturing images used in a facial recognition system are provided. The system and method are configured to generate a sequential set of control signals configured to cause a camera to capture a corresponding sequential set of probe images of a face of an individual. Each control signal in the sequential set of control signals is configured to cause the camera to capture a probe image of the sequential set of probe images using a different exposure time. The different exposure times associated with the sequential set of control signals together form a predetermined profile configured to enable capture of a usable image from the sequential set of probe images despite variation in at least one of an amount of light and a skin tone of the face of the individual.

Abstract: A system including a configurable memory controller, a memory interface, and a configurable high speed communications fabric comprising a plurality of interconnect stations arranged in an array and operable to implement a plurality of pipelined buses, where the configurable memory controller is operably coupled to the configurable high speed communications fabric using a first interconnect station of the plurality of interconnect stations, where the memory interface is operably coupled to the configurable high speed communications fabric using a second interconnect station of the plurality of interconnect stations, where the plurality of interconnect stations are configured to satisfy a timing requirement of the memory interface, and where the configurable memory controller, the memory interface, and the configurable high speed communications fabric are associated with a configurable integrated circuit.

Abstract: According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.

Abstract: A multi-spectral photon converting imaging apparatus and method are disclosed. A plurality of photons in a first received band and a plurality of photons in a second received band are received by a first nanoparticle photon conversion material. The first nanoparticle photon conversion material converts the plurality of photons in the first received band to a plurality of photons in a first converted band, and the plurality of photons in the second received band to a plurality of photons in a second converted band. An image sensor receives the plurality of photons in the first converted band and the plurality of photons in the second converted band, and generates a digitized image of the scene based on the plurality of photons in the first converted band and the plurality of photons in the second converted band.

Abstract: Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.

Abstract: Methods, systems, and computer readable media for reducing the impact of false downlink control information (DCI) detection in long term evolution (LTE) physical downlink control channel (PDCCH) data are disclosed. According to one method, an LTE multi-UE simulator receives PDCCH data from an evolved node B (eNode B). The LTE multi-UE simulator applies blind DCI decoding to decode at least one DCI value from channel control elements that carry the PDCCH data. The LTE multi-UE simulator applies at least one false DCI detection countermeasure to identify as true or false DCIs from the DCIs detected using the blind decoding.

Abstract: A wind blade with a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members is provided. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via multiple tensioning members to both the chord wise members and span wise members.

Abstract: A system including a configurable memory controller, a memory interface, and a configurable high speed communications fabric comprising a plurality of interconnect stations arranged in an array and operable to implement a plurality of pipelined buses, where the configurable memory controller is operably coupled to the configurable high speed communications fabric using a first interconnect station of the plurality of interconnect stations, where the memory interface is operably coupled to the configurable high speed communications fabric using a second interconnect station of the plurality of interconnect stations, where the plurality of interconnect stations are configured to satisfy a timing requirement of the memory interface, and where the configurable memory controller, the memory interface, and the configurable high speed communications fabric are associated with a configurable integrated circuit.

Abstract: A method for forming a ceramic matrix composite (CMC) component for gas turbine engines. The method contemplates replacing a plurality of plies with insert material. The insert material can be partially cured or pre-cured and applied in place of a plurality of small plies or it may be inserted into cavities of a component in the form of a paste or a ply. The insert material is isotropic, being formed of a combination of matrix material and chopped fibers, tow, cut plies or combinations thereof. The use of the insert material allows for features such as thin edges (650) with thicknesses of less than about 0.030 inches and small radii such as found in corners (680, 710). The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert, resulting in fewer defects, such as wrinkles, and better dimensional control.

Abstract: A method of making a ceramic matrix composite blade includes laying up at least one ply of the plurality of fibrous ceramic plies in a preselected arrangement to form an airfoil and dovetail preform, laying up at least one additional ply of the plurality of fibrous ceramic plies on the airfoil and dovetail preform in a second preselected arrangement to form an integral platform as part of the non-rigidized blade preform, rigidizing the blade preform to form a rigidized blade preform, and densifying the rigidized blade preform to form a ceramic matrix composite blade having an integral platform structure. A tool for making the ceramic matrix composite blade and a ceramic matrix composite blade are also disclosed.

Abstract: A rotor blade for a wind turbine includes an internal support structure extending span-wise from a blade root to a blade tip. A plurality of ribs are fixed to and spaced along the internal support structure, with each rib extending in a generally chord-wise direction and having a generally aerodynamic blade contour. A plurality of chord-wise oriented fabric strips are affixed to the ribs in a tensioned state, wherein the fabric strips define an aerodynamic outer skin of the rotor blade.

Abstract: A wind blade with a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members is provided. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via multiple tensioning members to both the chord wise members and span wise members.

Abstract: A three-dimensional preform, composite components formed with the preform, and processes for producing the preform and composite materials. The three-dimensional preform includes first and second sets of tows containing filaments. Each tow of the first set has a predetermined polygonal cross-sectional shape and is embedded within a temporary matrix. The preform is fabricated from the first and second sets of tows, in which the second set of tows are transverse to the first set of tows, adjacent tows of the second set are spaced apart to define interstitial regions therebetween, and the polygonal cross-sectional shapes of the first set of tows are substantially congruent to the cross-sectional shapes of the interstitial regions so as to substantially fill the interstitial regions.

Abstract: The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.

Abstract: Methods, systems, and computer readable media for reducing the impact of false downlink control information (DCI) detection in long term evolution (LTE) physical downlink control channel (PDCCH) data are disclosed. According to one method, an LTE multi-UE simulator receives PDCCH data from an evolved node B (eNode B). The LTE multi-UE simulator applies blind DCI decoding to decode at least one DCI value from channel control elements that carry the PDCCH data. The LTE multi-UE simulator applies at least one false DCI detection countermeasure to identify as true or false DCIs from the DCIs detected using the blind decoding.

Abstract: A MEMS spectrometer includes an optical substrate having a first face and a second face. A first semiconductor substrate is attached to the first face and includes a slit for passing incident light to the optical substrate, at least one integrated reflective grating, and at least one integrated detector array. A second semiconductor substrate is attached to the second face of the optical substrate and includes at least a first integrated mirror and a second integrated mirror. The first integrated mirror is positioned to receive the incident light transmitted by the optical substrate and to provide reflected light, and the integrated reflective grating, second integrated mirror and integrated detector array are positioned so that they are optically coupled to one another by the optical substrate to process the reflected light.

Abstract: A ceramic matrix composite with a ceramic matrix and a gradient layering of coating on ceramic fibers. The coating typically improves the performance of the composite in one direction while degrading it in another direction. For a SiC-SiC ceramic matrix composite, a BN coating is layered in a gradient fashion or in a step-wise fashion in different regions of the article comprising the ceramic. The BN coating thickness is applied over the ceramic fibers to produce varying desired physical properties by varying the coating thickness within differing regions of the composite, thereby tailoring the strength of the composite in the different regions. The coating may be applied as a single layer as a multi-layer coating to enhance the performance of the coating as the ceramic matrix is formed or infiltrated from precursor materials into a preform of the ceramic fibers.

Abstract: The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using a melt infiltration (MI) process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.

Abstract: The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.