Abstract: A method for automatically minimizing an undesirable motion of a workpiece during a machining operation, and a universal adaptive machining chatter control fixture that operates in accordance with the method. The method comprises the steps of mounting the workpiece to an active, supporting structure, and then machining the workpiece. During the step of machining, an undesirable motion of the workpiece is sensed in the supporting structure. Thereafter, a compensating motion is applied to the supporting structure for minimizing the undesirable motion of the workpiece. The chatter control fixture can be attached to various types of machine tool devices, without requiring that the machine tool devices be retrofitted, and operates to minimize undesirable motions of the workpiece independently of the machine tool devices.

Abstract: In accordance with the present invention, there is provided a riveting device. The riveting device is provided with a body defined by a body longitudinal axis and having a pressure port formed therein. The riveting device is further provided with a jaw defined by a jaw plane. The jaw has first and second jaw extensions with the first jaw extension having a jaw plunger orifice extending therethrough. The riveting device is further provided with an angular attachment having an attachment plunger orifice extending therethrough. The angular attachment is attached to the first jaw extension with the attachment plunger orifice being axially aligned with the jaw plunger orifice. The angular attachment is further attached to the body and formed to maintain the jaw plane at an angular orientation relative to the body longitudinal axis. The riveting device is further provided with a rivet plunger having opposing rivet and base ends.

Abstract: A method for assembling an aircraft includes determining a three-dimensional representation of a first aircraft structure and a second aircraft structure using an optical positioning device. A predicted mate of the first aircraft structure and the second aircraft structure is generated from the three-dimensional representation of the first and second aircraft structures using a processor. The method further includes adjusting the predicted mate of the first and second aircraft structures to enhance performance characteristics of the aircraft using the processor.

Abstract: A fastener injector (18) includes a plurality of tubes (86) operable to transfer a plurality of different sizes and types of fasteners (20) in a desired orientation. The injector also includes a receiver (88) operable to receive the fasteners (20) in the desired orientation from the tubes (86). The receiver (88) includes a plurality of receiver fingers (90) operable to receive the fasteners (20) from the tubes (86) and retain the fasteners (20) in the desired orientation. An injector blade (106) is operable to transfer the fasteners (20) in the desired orientation from the receiver (88) to a fastener installation device.

Abstract: In accordance with the present invention, there is provided a spectral nondestructive method for evaluating substrate surface characteristics of a sample substrate. The sample substrate has a sample substrate surface and a generally visually nontransmissive sample coating disposed on the sample substrate surface. The sample coating is transmissive within a first infrared spectral wavelength range and the sample substrate is reflective within the first infrared spectral wavelength range. The method begins with directing infrared radiation from an infrared radiation source towards the coated sample substrate. Specular and diffuse infrared radiation reflected from the coated sample substrate is collected. The reflected radiation is measured as a function of wavelength in the first infrared spectral wavelength range to obtain measured reflectance data representative of the reflectance of the coated sample substrate.

Abstract: A process for adhesively bonding two adherends to each other. The process includes directing a laser beam having characteristics substantially equivalent to a free electron laser to a respective surface of each of a first and/or second adherend to effectuate ablation of any organic and halogenated residues present on the surfaces, to glaze each surface, to form a substantially stable oxide layer thereon, and to microtexturize each surface such that a roughened surface with a tailored topography is formed on each surface. Thereafter, an adhesive is applied to at least one roughened surface and the two roughened surfaces are placed against each other such that the adhesive bonds the adherends along these respective roughened surfaces and provides a high-strength, long-term durability in most environments.

Abstract: An acoustic liner employable in jet engine housing construction for sound absorption such as for inclusion in nacelle components. The liner has a solid backface sheet having a surface to which is attached a first side of a honeycomb core structure. Attached to the opposing second side of the honeycomb core structure is a mesh structure to which is attached a perforated face sheet to be exposed to the exterior. As is thus apparent, the liner of the present invention provides a mesh situated below a protective perforate sheet. This construction produces an acoustic liner having substantially the efficiency of a linear liner system and the durability of a perforate face sheet system.