Abstract: A system for profile record generation of input records, the system comprising: a record processor which converts the input records into a data records suitable for the profile record generation; and a statistics engine for the generation of profile records based on the data records. Furthermore, system optimization can be obtained by use of a task control method that sub-divides the aggregations of profile records into units of work that can be individually performed, the method comprising: partitioning based on a pre-determined partitioning key associated with entities to be profiled, wherein the association between the partitioning key and the entities being profiled is varied in order to optimize the profiling performance.

Abstract: There is provided a method that includes (a) requesting first data for a first region of a display, and second data for second region of the display, (b) presenting first information in the first region, based on the first data, (c) commencing processing of an input that results from a user interaction with the first information, and (d) subsequent to the commencing processing of the input, presenting second information in the second region, based on the second data.

Abstract: Thermal anti-icing systems for aircraft and methods for fabricating such systems. The anti-icing systems have an integrated one-piece skin with passageways formed therein to supply a heated fluid to that portion of an aircraft structure where anti-icing is desired. The anti-icing system also has an integrated or separately supplied manifold for routing heating fluid to the anti-icing system flow passages. The anti-icing system can be used in the leading edges of such aircraft structures as wings, horizontal and vertical stabilizers, inboard and outboard slats, engine struts, and engine cowls. A method for fabricating of aircraft structures with integral anti-icing systems of the character just described is also disclosed.

Abstract: A method for making a thermal insulating structure for providing thermal insulation, structural load accommodation, and noise attenuation for surfaces in aerospace systems that are exposed to high temperatures is disclosed. Structure to be protected is a high-temperature solid back sheet to which is a honeycomb core having a perforated buried septum is bonded to a substrate. A layer of cast fiber-ceramic insulation is secured to the honeycomb core, filling portions of the core outward from the septum and extending beyond the outer face of the core. To absorb structural loads, a densified top coat overlies the insulating layer. To minimize the transmission of shear-inducing loads into the insulating layer, the outer face of the honeycomb core has an irregular surface. Core cell vents extending through the walls of adjacent cells provide a controlled airspace between the back sheet and the buried septum through which a fluid coolant may be circulated.

Abstract: A thermal insulating structure for providing thermal insulation, structural load accommodations, and noise attenuation for surfaces in aerospace systems that are exposed to high temperatures. At the side adjacent the structure to be protected is a high-temperature solid back sheet to which is adhesively bonded a honeycomb core having a perforated buried septum. A layer of cast fiber-ceramic insulation is secured to the honeycomb core, filling portions of the core outward from the septum and extending beyond the outer face of the core. To absorb structural loads, a densified top coat overlies the insulating layer. To minimize the transmission of shear-inducing loads into the insulating layer, the outer face of the honeycomb core has an irregular surface. Core cell vents extending through the walls of adjacent cells provide a controlled airspace between the back sheet and the buried septum through which a fluid coolant may be circulated.

Abstract: A load-bearing composite material structure (2, 2') has a plurality of layers of composite material. Each layer includes a matrix material (4) that maintains its structural integrity at 1200.degree. F. for at least five minutes. Preferred matrix materials are polyimide resins. Outer layers that will be directly exposed to a fire are reinforced with a woven fabric (8) that is sufficiently flame resistant and has a sufficiently fine weave to prevent flame penetration at 2000.degree. F. for at least fifteen minutes. The woven fabric (8) is preferably ceramic. The rest of the layers are reinforced with a fibrous material (6) to provide the necessary structural strength. The layers may be laminate cured together to form a single, integral structure (2) or such laminates adhesively bonded to a honeycomb (12).

Abstract: In an aircraft, a jet engine is carried by a frame (4), and the engine core casing (18B) acts as a beam. An engine core cowl (30) is made of a composite material that maintains structural strength within a given temperature range. The outer surface of the cowl (30) is cooled by the ambient airstream. The sidewall (32) of the cowl (30) is stiffened by a plurality of beams on its inner surface, preferably including axial beams (34) and circumferential beams (38). The beams (34,38) are tubular and have interconnecting passageways (37,39). The cowl (30) is connected to and structurally integrated with the engine casing. Cooling air is aspirated through the passageways (37,39) to maintain the inner portions of the beams (34,38) at essentially the same temperature as the outer surface of the sidewall (32). The flow of cooling air is metered. The cowl (30) acts as a beam and shares bending loads with the engine-casing.