Abstract: A towrope winch with a safety shutoff device includes a winch configured to wind a rope; and a safety shutoff device which deactivates the winch if, during winding of the rope, a foreign object enters a winch intake along with the rope to actuate the safety shutoff device.

Abstract: A towrope winch with a safety shutoff device includes a winch configured to wind a rope; and a safety shutoff device which deactivates the winch if the rope moves outside a designated range of angles relative to an intake of the winch.

Abstract: A system for starting from a dead start position may comprise a towrope winch, and a computing device configured to send and receive data to and from the towrope winch, in which the computing device is configured to operate the towrope winch and watercraft based on data inputted by the user to the computing device. A computer program product for operating a towrope winch from a dead start position may comprise a computer usable medium having computer usable program code embodied therewith, the computer usable program code comprising computer usable program code configured to prompt a user to enter data regarding the operation of the towrope winch from a dead start, and computer usable program code configured to operate the towrope winch based on data inputted by the user.

Abstract: A slider apparatus integral with a slidable member and a method for integrating the slider apparatus with the slidable member. The slider apparatus integrated with the slidable member may be configured to slidably couple with and be structurally supported by a fixed structure. The slider apparatus may comprise a primary slider component made of composite material and at least one chamfered element bonded to the primary slider component. The slidable member may comprise the slider apparatus, a core assembly, a plurality of composite material plies wrapped around the slider apparatus and core assembly and cured therewith, and at least one low-friction slider shoe removably attached to the primary slider component outward of the plurality of composite material plies.

Abstract: A system for controlling a towrope winch may comprise a computing device configured to send and receive data to and from the towrope winch, and a towrope winch application configured to operate on the computing device, in which the computing device is configured to operate the towrope winch based on data inputted by the user to the towrope winch application. A towrope winch user interface may comprise a processor configured to send and receive data to and from a towrope winch, and a towrope winch application configured to operate with the processor, in which the processor is configured to operate the towrope winch based on data inputted by the user to the towrope winch application.

Abstract: A system for controlling a towrope winch may comprise an electronic user interface selectively coupled to the towrope winch in which the user interface is configured to send and receive data to and from the towrope winch. A towrope winch user interface may comprise a processor configured to control said towrope winch, and a number of memory devices electrically coupled to the processor, in which the user interface is configured to send and receive data to and from the towrope winch. A mobile communications device may comprise a processor configured to control a towrope winch, a number of memory devices electrically coupled to the processor, and a tow system port configured to provide signal transfer between the processor and the towrope winch coupled to the mobile communications device, in which the mobile communications device is configured to send and receive data.

Abstract: A mandrel is disclosed for fabricating a monolithic composite nacelle panel for use on an airplane. Also disclosed is the method of constructing the mandrel, the method of assembling the mandrel, and the method of disassembling the mandrel.

Abstract: A method of constructing, assembling and disassembling a mandrel for fabricating a monolithic composite nacelle panel for use on an airplane comprises attaching a first fairing bar including an exposed ball roller assembly to a tilting plate; attaching a first outer section to said first fairing bar; attaching a second outer section to said first fairing bar; attaching a center section to said first outer section and said second outer section; attaching a nozzle section to said first fairing bar and positioned adjacent an inner wall of said first outer section, an inner wall of said center section, and an inner wall of said second outer section; attaching a second fairing bar to said first outer section, said center section, and said second outer section; and attaching a cavity section to said second fairing bar.

Abstract: A pinmat (12) for perforating a composite laminate sheet (20). The pinmat (12) includes a mat portion (22) and a series of pins (24) extending from the mat portion (22). Each pin (24) has a shank portion (30) extending from the mat portion (22) and a tip portion (32) extending from the shank portion (30). The tip portion (32)includes a base portion (34) extending from the shank portion (30), an accelerating portion (36) extending from the base portion (34), and a piercing portion (38) extending from the accelerating portion (36). The piercing portion (38) is utilized for penetrating the composite laminate sheet (20) within a substantially low range of applied pressure for forming a hole within the composite laminate sheet (20). Moreover, the accelerating portion (36) is utilized for penetrating the composite laminate sheet (20) at a substantially high speed for forcing the base portion (34) into the composite laminate sheet (20) within the substantially low range of applied pressure.

Abstract: A computer-implemented method for providing on-line ultrasonically scanned images of composite parts for immediate feedback in a manufacturing environment is discussed. The scanned images are edited to indicate each deficiency that has been repaired on a previously assembled composite part. Quality assurance personnel enter data associated with each composite part and verify the data content. Repair personnel enter data associated with correcting an identified deficiency of the composite part. Historical data suitable for developing statistics and trends are stored for each type of composite part. When queries are launched, the statistical and trend data is filtered to produce reports that are displayed. That is, reports are generated that identify particular statistics and trends. The scan image and data associated with a composite part are linked together for cross-referencing and stored in a database that is accessible by client and server computers on a network.

Abstract: A method of forming a composite acoustic panel (26). The method begins by arranging a perforated sheet (54) on a convex lay-up mandrel (70), arranging a core material (62, 74) on the perforated sheet (54), and curing the perforated sheet (54) and the core material (62, 74) to form a composite acoustic core (60) having a lay-up mandrel side and an opposite upper side. Composite sheets (96, 98) are then arranged on a concave lay-up mandrel. The composite acoustic core (60) is arranged on the composite sheets (96, 98) with the opposite upper side of the acoustic core (60) against the composite sheets (96, 98). The composite acoustic core (60) and the composite sheets (96, 98) are then cured so as to form the acoustic panel (26). A sacrificial sheet (76) can be added to upper side of the core material (62, 74) prior to curing the perforated sheet (54) and the core material (62, 74). The sacrificial sheet (76) preferably has a low coefficient of thermal expansion.

Abstract: An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).

Abstract: An outer cowl panel (24) for an engine nacelle (20). The outer cowl panel (24) includes integral track fairings (30) at aft side edges of the outer cowl panel. The outer cowl panel (24) also includes a chamfered leading edge having outer face sheets (88A, 88B) that extend over the leading edges of a stepped stack of prepreg sheets (88C, 88D, 88E, 88F).

Abstract: An improved acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a new reinforcement structure, or pre-cured doubler (62) therein. The pre-cured doubler (62) is arranged to receive a load applied to the acoustic panel (26), and includes a face sheet (64) connected to a structural attachment area (52) of the perforated composite inner sheet (54). A structurally-reinforced core (63) is connected the face sheet (64). Preferably, the width of the face sheet (64) in an air flow direction of the acoustic panel (26) is substantially equal to the width of the structurally reinforced core (63) in the air flow direction. The pre-cured doubler (62) provides increase acoustic area in parts of the acoustic panel adjacent to attachment fittings (46). Expanded epoxy (87a) is also used to reinforce side edges and selected areas of the acoustic core (60) for the acoustic panel (26).

Abstract: A cascade assembly (14) for use in a thrust reversing mechanism (16) of a jet engine (18) includes at least one group of substantially identically-shaped cascade elements (28) each in the shape of a predefined polygon. The cascade elements (28) are positioned in an array, wherein each cascade element (28) in the group may be interchanged in a location in the array with any other cascade element (28) in the group. In a first preferred embodiment, the predefined polygon is a regular polygon and each cascade element (28) is rotatable in its array position about an axis generally normal to the cascade element (28). The array substantially approximates sections of two intersecting spheres, wherein a central axis of the array is generally coincident with the longitudinal axis of the jet engine (18).